Propeller Owner's Manual and Logbook

Transcription

1 Manual No Revision 22 July 2016 Propeller Owner's Manual and Logbook Compact Models with Aluminum Blades Constant Speed, Non-Counterweighted ( )HC - ( )( )Y( ) - 1( ) Constant Speed, Counterweighted ( )HC - ( )( )Y( ) - 4( ) Constant Speed and Feathering ( )HC - ( )( )Y( ) - 2( ) Constant Speed and Feathering, Turbine ( )HC - ( )( )Y( ) - 5( ) Hartzell Propeller Inc. One Propeller Place Piqua, OH U.S.A. Ph: (Hartzell Propeller Inc.) Ph: (Product Support) Product Support Fax:

2 (This page is intentionally blank.) 1999, 2000, 2002, 2003, 2004, 2005, 2006, 2009, 2012, 2013, 2014, 2015, Hartzell Propeller Inc. - All rights reserved COVER Inside Cover Rev. 22 Jul/16

3 As a fellow pilot, I urge you to read this Manual thoroughly. It contains a wealth of information about your new propeller. The propeller is among the most reliable components of your airplane. It is also among the most critical to flight safety. It therefore deserves the care and maintenance called for in this Manual. Please give it your attention, especially the section dealing with Inspections and Checks. Thank you for choosing a Hartzell propeller. Properly maintained it will give you many years of reliable service. Jim Brown Chairman, Hartzell Propeller Inc. MESSAGE Page 1 Rev. 6 Sep/00

4 WARNING People who fly should recognize that various types of risks are involved; and they should take all precautions to minimize them, since they cannot be eliminated entirely. The propeller is a vital component of the aircraft. A mechanical failure of the propeller could cause a forced landing or create vibrations sufficiently severe to damage the aircraft, possibly causing it to become uncontrollable. Propellers are subject to constant vibration stresses from the engine and airstream, which are added to high bending and centrifugal stresses. Before a propeller is certified as being safe to operate on an airplane, an adequate margin of safety must be demonstrated. Even though every precaution is taken in the design and manufacture of a propeller, history has revealed rare instances of failures, particularly of the fatigue type. It is essential that the propeller is properly maintained according to the recommended service procedures and a close watch is exercised to detect impending problems before they become serious. Any grease or oil leakage, loss of air pressure, unusual vibration, or unusual operation should be investigated and repaired, as it could be a warning that something serious is wrong. MESSAGE Page 2 Rev. 6 Sep/00

5 For operators of uncertified or experimental aircraft an even greater level of vigilance is required in the maintenance and inspection of the propeller. Experimental installations often use propeller-engine combinations that have not been tested and approved. In these cases, the stress on the propeller and, therefore, its safety margin is unknown. Failure could be as severe as loss of propeller or propeller blades and cause loss of propeller control and/or loss of aircraft control. Hartzell Propeller Inc. follows FAA regulations for propeller certification on certificated aircraft. Experimental aircraft may operate with unapproved engines or propellers or engine modifications to increase horsepower, such as unapproved crankshaft damper configurations or high compression pistons. These issues affect the vibration output of the engine and the stress levels on the propeller. Significant propeller life reduction and failure are real possibilities. Frequent inspections are strongly recommended if operating with a non-certificated installation; however, these inspections may not guarantee propeller reliability, as a failing device may be hidden from the view of the inspector. Propeller overhaul is strongly recommended to accomplish periodic internal inspection. Visually examine blades for cracks. Examine hubs, with particular emphasis on each blade arm for cracks. Eddy current equipment is recommended for hub inspection, since cracks are usually not apparent. MESSAGE Page 3 Rev. 22 Jul/16

6 (This page is intentionally blank.) MESSAGE Page 4 Rev. 22 Jul/16

7 REVISION HIGHLIGHTS Revision 22, dated July 2016, incorporates the following: COVER Revised to match the manual revision MESSAGE Made language/format changes REVISION HIGHLIGHTS Revised to detail the contents of the manual revision SERVICE DOCUMENTS LIST Revised to match the manual revision AIRWORTHINESS LIMITATIONS Revised to correct a typographical error LIST OF EFFECTIVE PAGES Revised to match the manual revision TABLE OF CONTENTS Revised to match the manual revision DESCRIPTION AND OPERATION Revised the section "Aluminum Hub Propeller Model Identification" Revised the section "Aluminum Blade Model Identification" INSTALLATION AND REMOVAL Revised section 6, "Spinner Installation Added new Figure Revised the instructions for "Installing Spinner Assembly C-3567-(4,8) With a D (P) Spinner Dome" Revised the instructions for "Installing a Two-Piece Spinner Dome (Procedure 1)" and "Installing a Two-Piece Spinner Dome (Procedure 2)" Made other language/formatting changes INSPECTION AND CHECK Revised the section "Tachometer Inspection" MAINTENANCE PRACTICES Incorporated Service Letter HC-SL Added a Caution to the section "Modifying Spinner Bulkhead to Accommodate Dynamic Balance Weights" Revised the section "Placement of Balance Weights for Dynamic Balance" Made other language/formatting changes REVISION HIGHLIGHTS Page 5 Rev. 22 Jul/16

8 (This page is intentionally blank.) REVISION HIGHLIGHTS Page 6 Rev. 22 Jul/16

9 1. Introduction A. General Propeller Owner's Manual REVISIONS HIGHLIGHTS (1) This is a list of current revisions that have been issued against this manual. Please compare it to the RECORD OF REVISIONS page to make sure that all revisions have been added to the manual. B. Components (1) Revision No. indicates the revisions incorporated in this manual. (2) Issue Date is the date of the revision. (3) Comments indicates the level of the revision. (a) New Issue is a new manual distribution. The manual is distributed in its entirety. All the page revision dates are the same and no change bars are used. (b) Reissue is a revision to an existing manual that includes major content and/or major format changes. The manual is distributed in its entirety. All the page revision dates are the same and no change bars are used. (c) Major Revision is a revision to an existing manual that includes major content or minor content changes over a large portion of the manual. The manual is distributed in its entirety. All the page revision dates are the same, but change bars are used to indicate the changes incorporated in the latest revision of the manual. (d) Minor Revision is a revision to an existing manual that includes minor content changes to the manual. Only the revised pages of the manual are distributed. Each page retains the date and the change bars associated with the last revision to that page. REVISION HIGHLIGHTS Page 7 Rev. 22 Jul/16

10 Revision No. Issue Date Comments Rev. 5 Jan/99 Major Revision Rev. 6 Sep/00 Minor Revision Rev. 7 Oct/02 Major Revision Rev. 8 Jun/03 Minor Revision Rev. 9 Aug/03 Minor Revision Rev. 10 Nov/03 Minor Revision Rev. 11 Dec/04 Minor Revision Rev. 12 Apr/05 Minor Revision Rev. 13 Aug/06 Minor Revision Rev. 14 Jan/09 Minor Revision Rev. 15 Jul/09 Minor Revision Rev. 16 Oct/09 Minor Revision Rev. 17 Jul/12 Minor Revision Rev. 18 Feb/13 Minor Revision Rev. 19 Nov/13 Minor Revision Rev. 20 Mar/14 Minor Revision Rev. 21 Mar/15 Minor Revision Rev. 22 Jul/16 Minor Revision REVISION HIGHLIGHTS Page 8 Rev. 22 Jul/16

11 RECORD OF REVISIONS Rev. No. Issue Date Date Inserted Inserted By 7 Oct/02 Oct/02 HPI 8 Jun/03 Jun/03 HPI 9 Jul/03 Jul/03 HPI 10 Nov/03 Nov/03 HPI 11 Dec/04 Dec/04 HPI 12 Apr/05 Apr/05 HPI 13 Aug/06 Aug/06 HPI 14 Jan/09 Jan/09 HPI 15 Jul/09 Aug/09 HPI 16 Oct/09 Oct/09 HPI 17 Jul/12 Jul/12 HPI 18 Feb/13 Feb/13 HPI 19 Nov/13 Nov/13 HPI 20 Mar/14 Mar/14 HPI 21 Mar/15 Mar/15 HPI 22 Jul/16 Jul/16 HPI RECORD OF REVISIONS Page 9 Rev. 6 Sep/00

12 RECORD OF REVISIONS Rev. No. Issue Date Date Inserted Inserted By RECORD OF REVISIONS Page 10 Rev. 6 Sep/00

13 RECORD OF TEMPORARY REVISIONS TR Issue Date Inserted Date Removed No. Date Inserted By Removed By RECORD OF TEMPORARY REVISIONS Page 11 Rev. 6 Sep/00

14 RECORD OF TEMPORARY REVISIONS TR Issue Date Inserted Date Removed No. Date Inserted By Removed By RECORD OF TEMPORARY REVISIONS Page 12 Rev. 6 Sep/00

15 SERVICE DOCUMENTS LIST CAUTION 1: CAUTION 2: DO NOT USE OBSOLETE OR OUTDATED INFORMATION. PERFORM ALL INSPECTIONS OR WORK IN ACCORDANCE WITH THE MOST RECENT REVISION OF THE SERVICE DOCUMENT. INFORMATION CONTAINED IN A SERVICE DOCUMENT MAY BE SIGNIFICANTLY CHANGED FROM EARLIER REVISIONS. USE OF OBSOLETE INFORMATION MAY CREATE AN UNSAFE CONDITION THAT MAY RESULT IN DEATH, SERIOUS BODILY INJURY, AND/OR SUBSTANTIAL PROPERTY DAMAGE. REFER TO THE APPLICABLE SERVICE DOCUMENT INDEX FOR THE MOST RECENT REVISION LEVEL OF THE SERVICE DOCUMENT. THE INFORMATION FOR THE DOCUMENTS LISTED INDICATES THE REVISION LEVEL AND DATE AT THE TIME THAT THE DOCUMENT WAS INITIALLY INCORPORATED INTO THIS MANUAL. INFORMATION CONTAINED IN A SERVICE DOCUMENT MAY BE SIGNIFICANTLY CHANGED FROM EARLIER REVISIONS. REFER TO THE APPLICABLE SERVICE DOCUMENT INDEX FOR THE MOST RECENT REVISION LEVEL OF THE SERVICE DOCUMENT. Service Document Number Service Bulletins HC-SB HC-SB HC-SB HC-SB HC-SB Incorporation Rev/Date Rev. 11, Dec/04 Rev. 17, Jul/12 Rev. 21, Mar/15 Rev. 17, Jul/12 Rev. 21, Mar/15 Page 13 Rev. 21 Mar/15 SERVICE DOCUMENTS LIST

16 SERVICE DOCUMENTS LIST, CONTINUED Service Document Number Service Letters HC-SL , R3 HC-SL HC-SL HC-SL HC-SL Incorporation Rev/Date Rev. 21, Mar/15 Rev. 17, Jul/12 Rev. 21, Mar/15 Rev. 17, Jul/12 Rev. 22, Jul/16 SERVICE DOCUMENTS LIST Page 14 Rev. 22 Jul/16

17 AIRWORTHINESS LIMITATIONS The Airworthiness Limitations section is FAA approved and specifies maintenance required under 14 CFR and of the Federal Aviation Regulations unless an alternative program has been FAA approved. FAA APPROVED by: date: Manager, Chicago Aircraft Certification Office, ACE-115C Federal Aviation Administration Rev. No. Description of Revision Adds airworthiness limitation information from Hartzell 15 Overhaul Manual 113B ( ) and Hartzell Overhaul Manual 117D ( ) 16 Added cylinder life limits for propeller model HC-C(2,3)YR-4(B,C)F/FC8477-4R and corrected the engine model number for Aviatt Pitts S-2S,S-2B 19 Added blade life limits for propeller models HC-(C,F,M)2YR-1BFP/F7499 and HC-C2YR-1BF/F7666A-2 22 Corrected the engine model number for propeller model HC-(C,F,M)2YR-1BFP/F7499 AIRWORTHINESS LIMITATIONS Page 15 Rev. 22 Jul/16

18 AIRWORTHINESS LIMITATIONS 1. Replacement Time (Life Limits) A. The FAA establishes specific life limits for certain component parts, as well as the entire propeller. Such limits require replacement of the identified parts after a specified number of hours of use. B. The following data summarizes all current information concerning Hartzell life limited parts as related to propeller models affected by this manual. These parts are not life limited on other installations; however, time accumulated toward life limit accrues when first operated on aircraft/ engine/propeller combinations listed, and continues regardless of subsequent installations (which may or may not be life limited). FAA APPROVED by: date: Manager, Chicago Aircraft Certification Office, ACE-115C Federal Aviation Administration AIRWORTHINESS LIMITATIONS Page 16 Rev. 22 Jul/16

19 AIRWORTHINESS LIMITATIONS (1) The following list specifies life limits for blades only. Associated hub parts are not affected. Blade models shown are life limited only on the specified applications. Aircraft/Engine/Propeller Aircraft: Aviat Pitts S-2S Engine: Lycoming AEIO-540-D4A5 Propeller: HC-C2YR-4CF/FC8477A-4 Aircraft: Aviat Pitts S-2B Engine: Lycoming AEIO-540-D4A5 Propeller: HC-C2YR-4CF/FC8477A-4 Aircraft: SOCATA TB-30 Engine: Lycoming AEIO-540-L1B5D Propeller: HC-C2YR-4CF/FC Aircraft: Twin Commander Aircraft Models 500(B,S,U) as modified by Merlyn Products, Inc. Engine: Lycoming Models TIO-540-J2B and -J2BD Propeller: HC-C4YR-2/FC6660(K) Aircraft: Aerostar aircraft Models PA60-601(P), 602P as modified by Machen Engine: Lycoming (T)IO-540Series Models Propeller: HC-C4YR-2(L)/F(J)C6660(B,K) Blade Life Limit 2,000 hours 2,000 hours 4,000 hours 10,500 hours 10,500 hours FAA APPROVED by: date: Manager, Chicago Aircraft Certification Office, ACE-115C Federal Aviation Administration AIRWORTHINESS LIMITATIONS Page 17 Rev. 22 Jul/16

20 AIRWORTHINESS LIMITATIONS (2) The following list specifies life limits for blades only. Associated hub parts are not affected. Blade models shown are life limited only on the specified engine. Propeller/Engine Propeller: HC-(C,F,M)2YR-1BFP/F7499 Engine: Engine Components, Inc. (ECI) (I)OX-360-( ) 8.5:1 to 10.2:1 Compression Ratio Max Diameter 74 inches Min. Diameter 72 inches Operating Restriction: Do not operate above 24 manifold pressure below 2450 RPM Propeller: HC-(C,F,M)2YR-1BFP/F7499 Engine: Engine Components, Inc. (ECI) (I)OX-370-( ) 8.5:1 Compression Ratio Max Diameter 74 inches Min. Diameter 72 inches Operating Restriction: Do not operate above 24 manifold pressure below 2450 RPM Blade Life Limit 10,000 hours 10,000 hours FAA APPROVED by: date: Manager, Chicago Aircraft Certification Office, ACE-115C Federal Aviation Administration AIRWORTHINESS LIMITATIONS Page 18 Rev. 22 Jul/16

21 AIRWORTHINESS LIMITATIONS Propeller: Propeller/Engine HC-C2YR-1BF/F7666A-2 Engine: Lycoming O-360-A1A rated at 180hp at 2700 RPM equipped with Lightspeed Plasma II electronic ignition Max. Diameter 74 inches Min. Diameter 72 inches Operating Restriction: Avoid continuous operation between 2000 and 2250 RPM. Operation above 2600 RPM is limited to takeoff. As soon as practical after takoff, the RPM should be reduced to 2600 RPM or less. Blade Life Limit 8,700 hours FAA APPROVED by: date: Manager, Chicago Aircraft Certification Office, ACE-115C Federal Aviation Administration AIRWORTHINESS LIMITATIONS Page 19 Rev. 22 Jul/16

22 AIRWORTHINESS LIMITATIONS (3) The following list specifies life limits for propeller hubs only. Hubs listed are life limited only on the specified applications. Aircraft/Engine/Propeller Aircraft: Aviatt Pitts S-2S Engine: Lycoming AEIO-540-D4A5 Propeller: HC-C2YR-4CF/FC8477A-4 Aircraft: Aviatt Pitts S-2B Engine: Lycoming AEIO-540-D4A5 Propeller: HC-C2YR-4CF/FC8477A-4 Aircraft: SOCATA TB-30 Engine: Lycoming AEIO-540-L1B5D Propeller: HC-C2YR-4CF/FC Aircraft: SOCATA TB-30 Engine: Lycoming AEIO-540-L1B5D Propeller: HC-C2YR-4CF/FC Hub Unit Life Limit 2,000 hours 2,000 hours 4,000 hours ("A" suffix serial numbers) 16,000 hours ("B" suffix serial numbers) (4) The following list specifies life limits for cylinder part number only. Cylinders listed are life limited only on the specified applications. Aircraft/Engine/Propeller Aircraft: Hindustan HPT-32 Engine: Lycoming AEIO-540-D4B5 Propeller: HC-C(2,3)YR-4(B,C)F/FC8477-4R Cylinder Life Limit 2,000 hours FAA APPROVED by: date: Manager, Chicago Aircraft Certification Office, ACE-115C Federal Aviation Administration AIRWORTHINESS LIMITATIONS Page 20 Rev. 22 Jul/16

23 LIST OF EFFECTIVE PAGES Chapter Page Revision Date Cover Cover and Inside Cover Rev. 22 Jul/16 Message 1 and 2 Rev. 6 Sep/00 Message 3 and 4 Rev. 22 Jul/16 Revision Highlights 5 thru 8 Rev. 22 Jul/16 Record of Revisions 9 and 10 Rev. 6 Sep/00 Record of Temporary Revisions 11 and 12 Rev. 6 Sep/00 Service Documents List 13 Rev. 21 Mar/15 Service Documents List 14 Rev. 22 Jul/16 Airworthiness Limitations 15 thru 20 Rev. 22 Jul/16 List of Effective Pages 21 thru 24 Rev. 22 Jul/16 Table of Contents 25 thru 29 Rev. 21 Mar/15 Table of Contents 30 Rev. 22 Jul/16 Table of Contents 31 and 32 Rev. 21 Mar/15 Table of Contents 33 Rev. 22 Jul/16 Table of Contents 34 Rev. 21 Mar/15 Introduction 1-1 and 1-2 Rev. 21 Mar/15 Introduction 1-3 and 1-4 Rev. 18 Feb/13 Introduction 1-5 Rev. 17 Jul/12 Introduction 1-6 thru 1-20 Rev. 21 Mar/15 Description and Operation 2-1 Rev. 17 Jul/12 Description and Operation 2-2 Rev. 14 Jan/09 Description and Operation 2-3 thru 2-12 Rev. 13 Aug/06 Description and Operation 2-13 Rev. 14 Jan/09 Description and Operation 2-14 Rev. 13 Aug/06 Description and Operation 2-15 Rev. 7 Oct/02 Description and Operation 2-16 Rev. 22 Jul/16 Description and Operation 2-17 Rev. 12 Apr/05 Description and Operation 2-18 Rev. 15 Jul/09 Description and Operation 2-19 Rev. 12 Apr/05 Description and Operation 2-20 Rev. 22 Jul/16 Description and Operation 2-21 and 2-22 Rev. 16 Oct/09 Description and Operation 2-23 Rev. 12 Apr/05 Description and Operation 2-24 Rev. 16 Oct/09 Description and Operation 2-25 and 2-26 Rev. 17 Jul/12 Description and Operation 2-27 and 2-28 Rev. 14 Jan/09 Description and Operation 2-29 thru 2-31 Rev. 17 Jul/12 Description and Operation 2-32 Rev. 12 Apr/05 LIST OF EFFECTIVE PAGES Page 21 Rev. 22 Jul/16

24 LIST OF EFFECTIVE PAGES Chapter Page Revision Date Installation and Removal 3-1 and 3-2 Rev. 21 Mar/15 Installation and Removal 3-3 Rev. 22 Jul/16 Installation and Removal 3-4 Rev. 21 Mar/15 Installation and Removal and Rev. 21 Mar/15 Installation and Removal 3-5 Rev. 21 Mar/15 Installation and Removal 3-6 Rev. 14 Jan/09 Installation and Removal 3-7 Rev. 21 Mar/15 Installation and Removal 3-8 Rev. 14 Jan/09 Installation and Removal 3-9 Rev. 21 Mar/15 Installation and Removal 3-10 Rev. 14 Jan/09 Installation and Removal 3-11 Rev. 21 Mar/15 Installation and Removal 3-12 Rev. 14 Jan/09 Installation and Removal 3-13 Rev. 21 Mar/15 Installation and Removal 3-14 Rev. 14 Jan/09 Installation and Removal 3-15 Rev. 22 Jul/16 Installation and Removal 3-16 Rev. 14 Jan/09 Installation and Removal 3-17 Rev. 17 Jul/12 Installation and Removal 3-18 Rev. 15 Jul/09 Installation and Removal 3-19 and 3-20 Rev. 14 Jan/09 Installation and Removal 3-21 Rev. 17 Jul/12 Installation and Removal 3-22 Rev. 14 Jan/09 Installation and Removal 3-23 and 3-24 Rev. 21 Mar/15 Installation and Removal 3-25 and 3-26 Rev. 14 Jan/09 Installation and Removal 3-27 Rev. 17 Jul/12 Installation and Removal 3-28 thru 3-51 Rev. 21 Mar/15 Installation and Removal 3-52 and 3-53 Rev. 22 Jul/16 Installation and Removal 3-54 thru 3-57 Rev. 21 Mar/15 Installation and Removal 3-58 Rev. 22 Jul/16 Installation and Removal and Rev. 22 Jul/16 Installation and Removal 3-59 and 3-60 Rev. 22 Jul/16 Installation and Removal 3-61 and 3-62 Rev. 21 Mar/15 Installation and Removal 3-63 Rev. 22 Jul/16 Installation and Removal 3-64 Rev. 21 Mar/15 Installation and Removal 3-65 and 3-66 Rev. 22 Jul/16 Installation and Removal 3-67 thru 3-80 Rev. 21 Mar/15 Testing and Troubleshooting 4-1 thru 4-4 Rev. 20 Mar/14 Testing and Troubleshooting 4-5 Rev. 14 Jan/09 Testing and Troubleshooting 4-6 Rev. 17 Jul/12 LIST OF EFFECTIVE PAGES Page 22 Rev. 22 Jul/16

25 LIST OF EFFECTIVE PAGES Chapter Page Revision Date Testing and Troubleshooting 4-7 Rev. 14 Jan/09 Testing and Troubleshooting 4-8 thru 4-10 Rev. 17 Jul/12 Testing and Troubleshooting 4-11 thru 4-14 Rev. 14 Jan/09 Inspection and Check 5-1 and 5-2 Rev. 22 Jul/16 Inspection and Check 5-3 thru 5-10 Rev. 17 Jul/12 Inspection and Check and Rev. 21 Mar/15 Inspection and Check 5-11 Rev. 21 Mar/15 Inspection and Check 5-12 thru 5-17 Rev. 17 Jul/12 nspection and Check 5-18 Rev. 22 Jul/16 Inspection and Check 5-19 Rev. 17 Jul/12 nspection and Check 5-20 and 5-21 Rev. 22 Jul/16 Inspection and Check 5-22 thru 5-30 Rev. 17 Jul/12 Maintenance Practices 6-1 and 6-2 Rev. 22 Jul/16 Maintenance Practices 6-3 Rev. 17 Jul/12 Maintenance Practices 6-4 Rev. 14 Jan/09 Maintenance Practices 6-5 Rev. 21 Mar/15 Maintenance Practices 6-6 thru 6-12 Rev. 22 Jul/16 Maintenance Practices and Rev. 22 Jul/16 Maintenance Practices 6-13 thru 6-15 Rev. 17 Jul/12 Maintenance Practices 6-16 Rev. 16 Oct/09 Maintenance Practices and Rev. 16 Oct/09 Maintenance Practices 6-17 Rev. 16 Oct/09 Maintenance Practices 6-18 Rev. 14 Jan/09 Maintenance Practices 6-19 thru 6-21 Rev. 17 Jul/12 Maintenance Practices 6-22 Rev. 14 Jan/09 Maintenance Practices 6-23 thru 6-26 Rev. 17 Jul/12 Maintenance Practices 6-27 and 6-28 Rev. 14 Jan/09 Maintenance Practices 6-29 Rev. 17 Jul/12 Maintenance Practices 6-30 Rev. 14 Jan/09 Maintenance Practices 6-31 and 6-32 Rev. 22 Jul/16 Maintenance Practices 6-33 Rev. 17 Jul/12 Maintenance Practices 6-34 thru 6-46 Rev. 21 Mar/15 Anti-Ice and De-Ice Systems 7-1 thru 7-3 Rev. 14 Jan/09 Anti-Ice and De-Ice Systems 7-4 Rev. 13 Aug/06 Anti-Ice and De-Ice Systems 7-5 thru 7-8 Rev. 14 Jan/09 Records 8-1 thru 8-4 Rev. 14 Jan/09 LIST OF EFFECTIVE PAGES Page 23 Rev. 22 Jul/16

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27 TABLE OF CONTENTS MESSAGE...1 REVISION HIGHLIGHTS...5 RECORD OF REVISIONS...9 RECORD OF TEMPORARY REVISIONS...11 SERVICE DOCUMENTS LIST...13 AIRWORTHINESS LIMITATIONS...15 LIST OF EFFECTIVE PAGES...23 TABLE OF CONTENTS...27 INTRODUCTION Purpose Airworthiness Limitations Airframe or Engine Modifications Restrictions and Placards General A. Personnel Requirements B. Maintenance Practices C. Continued Airworthiness D. Propeller Critical Parts Reference Publications A. Hartzell Propeller Inc. Publications B. References to Hartzell Propeller Inc. Publications Definitions Abbreviations Hartzell Propeller Inc. Product Support Warranty Service Hartzell Propeller Inc. Recommended Facilities TABLE OF CONTENTS Page 25 Rev. 21 Mar/15

28 TABLE OF CONTENTS, CONTINUED DESCRIPTION AND OPERATION Description of Propeller and Systems A. System Overview Functional Description of Constant Speed Propeller Types A. Constant Speed, Non-Counterweighted Propellers ( )HC-( )( )Y( )-1( ) B. Constant Speed, Feathering Propellers ( )HC-( )( )Y( )-2( ) C. Constant Speed, Counterweighted (Aerobatic) Propellers ( )HC-( )( )Y( )-4( ) D. Constant Speed, Feathering, Turbine Propellers ( )HC-( )( )Y( )-5( ) Model Designation A. Aluminum Hub Propeller Model Identification B. Aluminum Blade Model Identification Governors A. Theory of Operation B. Governor Types C. Identification of Hartzell Propeller Inc. Governors Accumulator A. System Overview Propeller Ice Protection Systems A. Propeller Anti-ice System B. Propeller De-ice System INSTALLATION AND REMOVAL Tools, Consumables, and Expendables A. Tooling B. Consumables C. Expendables Pre-Installation A. Inspection of Shipping Package B. Uncrating TABLE OF CONTENTS Page 26 Rev. 21 Mar/15

29 TABLE OF CONTENTS, CONTINUED C. Inspection after Shipment D. Reassembly of a Propeller Disassembled for Shipment E. Air Charge Pressure Check (-2 and -5 Propellers) Spinner Pre-Installation A. General B. Installation of a Metal Spinner Bulkhead on the Propeller Hub C. Installation of a Composite Spinner Bulkhead on a Propeller Hub - Refer to Table 3-3 and Figure D. Spinner Adapter to Starter Ring Gear Installation Propeller Installation A. Flange Description B. Installation of D Flange Propellers C. Installation of F Flange Propellers D. Installation of N Flange Propellers E. Installation of L Flange Propellers, Except Model HC-E2YL-( ) F. Installation of HC-E2YL-( ) Propellers G. Installation of K and R Flange Propellers Damper Installation A. Installation of C-1576 Damper (Hartzell Propeller Inc. Kit A-1583) Spinner Installation A. Installing a Single Piece Spinner Dome, Except Spinner Assembly C-3567-(4,8) With a D (P) Spinner Dome B. Installing Spinner Assembly C-3567-(4,8) With a D (P) Spinner Dome C. Installing a Two-Piece Spinner Dome (Procedure 1) D. Installing a Two-Piece Spinner Dome (Procedure 2) Post-Installation Checks Spinner Removal A. Removal of Single Piece Spinner TABLE OF CONTENTS Page 27 Rev. 21 Mar/15

30 TABLE OF CONTENTS, CONTINUED B. Removal of Two-Piece Spinner C. Hub Mounted Spinner Bulkhead Removal D. Starter Ring Gear Spinner Adapter Removal Propeller Removal A. Removal of D Flange Propellers B. Removal of F Flange Propellers C. Removal of N Flange Propellers D. Removal of L Flange Propellers, Except Model HC-E2YL-( ) E. Removal of HC-E2YL-( ) Propellers F. Removal of K and R Flange Propellers TESTING AND TROUBLESHOOTING Operational Tests A. Initial Run-Up B. Static RPM Check C. Post-Run Check Propeller Ice Protection Systems A. Electric De-ice System B. Anti-ice System Troubleshooting A. Hunting and Surging B. Engine Speed Varies with Flight Attitude (Airspeed) C. Loss of Propeller Control (-1 propellers only) D. Loss of Propeller Control (-2, -4 or -5 propellers) E. Failure to Feather or Feathers Slowly (-2 or -5 propellers only) F. Failure to Unfeather G. Start Locks (Anti-feather Latches) Fail to Latch on Shutdown (-2 and some -5 feathering propellers only) H. Vibration TABLE OF CONTENTS Page 28 Rev. 21 Mar/15

31 I. Propeller Overspeed J. Propeller Underspeed K. Oil or Grease Leakage INSPECTION AND CHECK Pre-Flight Checks Post-Flight Checks A. HC-C2YR-2CLUF/FLC7666A-4 Propellers Installed on OMA SUD Skycar Aircraft Operational Checks Required Periodic Inspections and Maintenance A. Periodic Inspections B TABLE OF CONTENTS, CONTINUED Blade Inspection for an HC-C2YR-2CLUF/FLC7666A-4 Propeller Installed on OMA SUD Skycar Aircraft C. Spinner Bulkhead Inspection for an HC-E3YR-1RF Propeller Installed on S.N.A. Inc. Seawind Aircraft D. Low Pitch Stop Hardware Inspection for a PHC-C3YF-2UF/FC7693DFB Propeller E. Periodic Maintenance F. Airworthiness Limitations G. Overhaul Periods Inspection Procedures A. Blade Damage B. Grease or Oil Leakage C. Vibration D. Tachometer Inspection E. Blade Track F. Loose Blades G. Corrosion H. Spinner Damage I. Electric De-ice System J. Anti-ice System TABLE OF CONTENTS Page 29 Rev. 21 Mar/15

32 TABLE OF CONTENTS, CONTINUED 6. Special Inspections A. Overspeed/Overtorque B. Lightning Strike C. Foreign Object Strike D. Fire Damage or Heat Damage Long Term Storage MAINTENANCE PRACTICES Cleaning A. General Cleaning B. Spinner Cleaning and Polishing Lubrication A. Lubrication Intervals B. Lubrication Procedure C. Approved Lubricants Air Charge (-2 and -5 Propellers) A. Charging the Propeller B. Basic pressures Unfeathering Accumulator Air Charge A. Charging a Hartzell Propeller Inc. Accumulator Blade Repairs A. Repair of Nicks or Gouges B. Repair of Bent Blades Painting After Repair A. General B. Painting of Aluminum Blades Dynamic Balance A. Overview B. Inspection Procedures Before Balancing C. Modifying Spinner Bulkhead to Accommodate Dynamic Balance Weights D. Placement of Balance Weights for Dynamic Balance TABLE OF CONTENTS Page 30 Rev. 22 Jul/16

33 8. Propeller Low Pitch Setting A. Low Pitch Stop - All Propeller Models B. Max. RPM (Static) Low Pitch Stop Adjustment C. Modification of the Low Pitch Stop Hardware Propeller High Pitch Settings A. High Pitch (Min. RPM) Stop or Feathering Pitch Stop Start Lock Settings A. Start Lock Pitch Stop Propeller Ice Protection Systems A. Electric De-ice System B. Anti-ice System ANTI-ICE AND DE-ICE SYSTEMS Introduction A. Propeller De-ice System B. Propeller Anti-ice System System Description A. De-ice System B. Anti-ice System De-ice System Functional Tests Anti-ice System Functional Tests De-ice and Anti-ice System Inspections A. De-ice System Inspections B. Anti-ice System Inspections De-ice and Anti-ice System Troubleshooting A. De-ice System Troubleshooting B. Anti-ice System Troubleshooting RECORDS Introduction Record Keeping A. Information to be Recorded TABLE OF CONTENTS Page 31 Rev. 21 Mar/15

34 LIST OF FIGURES Cutaway of -1 Series Constant Speed Non-Counterweighted Propeller ( )HC-( )( )Y( )-1( )... Figure Cutaway of -2 Series Constant Speed Feathering Propeller ( )HC-( )( )Y( )-2... Figure Cutaway of -4 Series Constant Speed, Counterweighted (Aerobatic) Propeller ( )HC-( )( )Y( )-4( )... Figure Cutaway of -5 Series Constant Speed, FeatheringTurbine Propeller ( )HC-( )( )Y( )-5( )... Figure Governor in Onspeed Condition... Figure Governor in Underspeed Condition... Figure Governor in Overspeed Condition... Figure Feathering Governor... Figure Synchronizer/Synchrophaser Governor... Figure Governor/Accumulator System... Figure Determining Torque Value When Using Torquing Adapter... Figure Diagram of Torquing Sequence for Propeller Mounting Hardware... Figure Hub Clamping Bolt Location... Figure Metal Spinner Bulkhead and Spinner Mounting (Hub Mounted Spinner)... Figure Composite Bulkhead and Spinner Mounting (Hub Mounted Spinner)... Figure Spinner Adapter and Spinner Mounting (Starter Ring Gear Mount)... Figure D Flange Propeller Mounting... Figure F and N Flange Propeller Mounting... Figure TABLE OF CONTENTS Page 32 Rev. 21 Mar/15

35 LIST OF FIGURES, CONTINUED L, K, and R Flange Propeller Mounting... Figure Damper Installation... Figure Installing the Spacer Base and Spinner Mounting Spacers... Figure Install the Plastic Forward Bulkhead and Pre-fit the Spinner Dome...Figure Optional Tape on the Forward Bulkhead... Figure Spinner Dome Mounting Hole Alignment... Figure Two-Piece Spinner Mounting (Procedure 1)... Figure Two-Piece Spinner Mounting (Procedure 2)... Figure Spinner Dome to Bulkhead Mounting Hole Alignment... Figure Checking Blade Track... Figure Blade Play... Figure Reciprocating Engine Overspeed Limits... Figure Turbine Engine Overspeed Limits... Figure Turbine Engine Overtorque Limits... Figure Lubrication Fitting and Air Charge Valve Location... Figure Lubrication Fitting... Figure Lubrication Label... Figure Counterweighted vs Non-Counterweighted Blades... Figure Unfeathering Accumulator... Figure Repair Limitations... Figure Low Pitch Stop Adjustment (-1, -4)... Figure Low Pitch Stop Adjustment (-2, -5) For Propellers That Use a Two-piece Spinner Dome... Figure Low Pitch Stop Adjustment (-2, -5) For Propellers That Use a One-piece Spinner Dome... Figure Hex Nut Configuration... Figure TABLE OF CONTENTS Page 33 Rev. 22 Jul/16

36 LIST OF TABLES Torque Table... Table Metal Spinner Bulkhead Mounting Hardware... Table Composite Spinner Bulkhead Mounting Hardware... Table Propeller/Engine Flange O-rings and Mounting Hardware... Table Spinner Dome and Spinner Cap Mounting Hardware... Table Air Charge Pressure... Table Air Charge Pressure... Table Air Charge Pressure... Table Air Charge Pressure... Table Air Charge Pressure... Table Air Charge Pressure... Table Air Charge Pressure... Table Air Charge Pressure... Table Air Charge Pressure... Table Air Charge Pressure... Table Accumulator Air Charge Pressure... Table Approved Touch-up Paints... Table TABLE OF CONTENTS Page 34 Rev. 21 Mar/15

37 INTRODUCTION - CONTENTS 1. Purpose Airworthiness Limitations Airframe or Engine Modifications Restrictions and Placards General A. Personnel Requirements B. Maintenance Practices C. Continued Airworthiness D. Propeller Critical Parts Reference Publications A. Hartzell Propeller Inc. Publications B. References to Hartzell Propeller Inc. Publications Definitions Abbreviations Hartzell Propeller Inc. Product Support Warranty Service Hartzell Propeller Inc. Recommended Facilities INTRODUCTION Page 1-1 Rev. 21 Mar/15

38 (This page is intentionally blank.) INTRODUCTION Page 1-2 Rev. 21 Mar/15

39 1. Purpose Propeller Owner's Manual A. This manual has been reviewed and accepted by the FAA. Additionally, the Airworthiness Limitations Section of this manual has been approved by the FAA. CAUTION: KEEP THIS MANUAL WITH THE PROPELLER OR THE AIRCRAFT UPON WHICH IT IS INSTALLED AT ALL TIMES. THE LOG BOOK RECORD WITHIN THIS MANUAL MUST BE MAINTAINED, RETAINED CONCURRENTLY, AND BECOME A PART OF THE AIRCRAFT AND ENGINE SERVICE RECORDS. B. This manual supports Hartzell Propeller Inc. Constant Speed and Constant Speed Feathering Compact series propellers with aluminum blades. (1) The purpose of this manual is to enable qualified personnel to install, operate, and maintain a Hartzell Propeller Inc. Constant Speed or Constant Speed Feathering Propeller. Separate manuals are available concerning overhaul procedures and specifications for the propeller. (2) This manual includes several design types. (a) Sample propeller and blade model designation within each design are included in the Description and Operation chapter of this manual. 1 Parentheses shown in the propeller model designations in this or other Hartzell Propeller Inc. publications indicate letter(s) and/or number(s) that may or may not be present because of different configurations permitted on the various aircraft installations. 2 Definitions of propeller model designations and further details of letters that may be present are shown in the Description and Operation chapter of this manual. (b) All propeller models included in this manual use aluminum propeller blades. Propellers that use composite blades are supported by Hartzell Propeller Inc. Owner s Manual 145 ( ). INTRODUCTION Page 1-3 Rev. 18 Feb/13

40 2. Airworthiness Limitations Propeller Owner's Manual A. Refer to the Airworthiness Limitations chapter of this manual for Airworthiness Limits information. 3. Airframe or Engine Modifications A. Propellers are approved vibrationwise on airframe and engine combinations based on tests or analysis of similar installations. This data has demonstrated that propeller stress levels are affected by airframe configuration, airspeed, weight, power, engine configuration and approved flight maneuvers. Aircraft modifications that can effect propeller stress include, but are not limited to: aerodynamic changes ahead of or behind the propeller, realignment of the thrust axis, increasing or decreasing airspeed limits, increasing or decreasing weight limits (less significant on piston engines), the addition of approved flight maneuvers (utility and aerobatic). B. Engine modifications can also affect the propeller. The two primary categories of engine modifications are those that affect structure and those that affect power. An example of a structural engine modification is the alteration of the crankshaft or damper of a piston engine. Any change to the weight, stiffness or tuning of rotating components could result in a potentially dangerous resonant condition that is not detectable by the pilot. Most common engine modifications affect the power during some phase of operation. Some modifications increase the maximum power output, while others improve the power available during hot and high operation (flat rating) or at off-peak conditions. Examples of such engine modifications include, but are not limited to: changes to the compressor, power turbine or hot section of a turboprop engine; and on piston engines, the addition or alteration of a turbocharger or turbonormalizer, increased compression ratio, increased rpm, altered ignition timing, electronic ignition, full authority digital electronic controls (FADEC), or tuned induction or exhaust. C. All such modifications must be reviewed and approved by the propeller manufacturer before obtaining approval on the aircraft. INTRODUCTION Page 1-4 Rev. 18 Feb/13

41 4. Restrictions and Placards Propeller Owner's Manual A. The propellers included in this manual may have a restricted operating range that requires a cockpit placard. 5. General (1) The restrictions, if present, will vary depending on the propeller, blade, engine, and/or aircraft model. (2) Review the propeller and aircraft type certificate data sheet (TCDS), Pilot Operating Handbook (POH), and any applicable Airworthiness Directives for specific information. A. Personnel Requirements (1) Personnel performing maintenance are expected to have sufficient training and certifications (when required by the applicable Aviation Authority) to accomplish the work required in a safe and airworthy manner. (2) Compliance to the applicable regulatory requirements established by the Federal Aviation Administration (FAA) or foreign equivalent is mandatory for anyone performing or accepting responsibility for any inspection and/or repair and/or overhaul of any Hartzell Propeller Inc. product. B. Maintenance Practices (1) The propeller and its components are highly vulnerable to damage while they are removed from the engine. Properly protect all components until they are reinstalled on the engine. (2) Never attempt to move the aircraft by pulling on the propeller. (3) Avoid the use of blade paddles. If blade paddles must be used, use at least two paddles. Do not put the blade paddle in the area of the de-ice or anti-icing boot when applying torque to a blade assembly. Put the blade paddle in the thickest area of the blade, just outside of the de-ice or anti-icing boot. Use one blade paddle per blade. (4) Use only the approved consumables, e.g., cleaning agents, lubricants, etc. INTRODUCTION Page 1-5 Rev. 17 Jul/12

42 (5) Safe Handling of Paints and Chemicals (a) Always use caution when handling or being exposed to paints and/or chemicals during propeller overhaul and maintenance procedures. (b) Before using paint or chemicals, always read the manufacturer s label on the container and follow specified instructions and procedures for storage, preparation, mixing, and application. (c) Refer to the product s Material Safety Data Sheet (MSDS) for detailed information about physical properties, health, and physical hazards of any chemical. (6) Observe applicable torque values during maintenance. (7) Approved corrosion protection followed by approved paint must be applied to all aluminum blades. For information concerning the application of corrosion protection and paint, refer to the Maintenance Practices chapter of this manual. Operation of blades without the specified coatings and finishes, i.e., polished blades, is not permitted. (8) Before installing the propeller on the engine, the propeller must be statically balanced. New propellers are statically balanced at Hartzell Propeller Inc.. Overhauled propellers must be statically balanced by the overhaul facility before return to service. (a) Dynamic balance is recommended, but may be accomplished at the discretion of the operator, unless specifically required by the airframe or engine manufacturer. 1 Perform dynamic balance in accordance with the Maintenance Practices chapter of this manual. 2 Additional procedures may be found in the aircraft maintenance manual. (9) As necessary, use a soft, non-graphite pencil or crayon to make identifying marks on components. INTRODUCTION Page 1-6 Rev. 21 Mar/15

43 (10) As applicable, follow military standard NASM33540 for safety wire, safety cable, and cotter pin general practices. Use (0.81 mm) diameter stainless steel safety wire unless otherwise indicated. CAUTION: DO NOT USE OBSOLETE OR OUTDATED INFORMATION. PERFORM ALL INSPECTIONS OR WORK IN ACCORDANCE WITH THE MOST RECENT REVISION OF THIS MANUAL. INFORMATION CONTAINED IN THIS MANUAL MAY BE SIGNIFICANTLY CHANGED FROM EARLIER REVISIONS. USE OF OBSOLETE INFORMATION MAY RESULT IN DEATH, SERIOUS BODILY INJURY, AND/OR SUBSTANTIAL PROPERTY DAMAGE. FOR THE MOST RECENT REVISION LEVEL OF THIS MANUAL, REFER TO THE HARTZELL PROPELLER INC. WEBSITE AT (11) The information in this manual revision supersedes data in all previously published revisions of this manual. (12) Refer to the airframe manufacturer s manuals in addition to the information in this manual because of possible special requirements for specific aircraft applications. INTRODUCTION Page 1-7 Rev. 21 Mar/15

44 (13) If the propeller is equipped with an ice protection system that uses components supplied by Hartzell Propeller Inc., applicable instructions and technical information for the components supplied by Hartzell Propeller Inc. can be found in the following publications available on the Hartzell Propeller Inc. website at (a) Hartzell Propeller Inc. Manual 180 ( ) - Propeller Ice Protection System Manual (b) Hartzell Propeller Inc. Manual 181 ( ) - Propeller Ice Protection System Component Maintenance Manual (c) Hartzell Propeller Inc. Manual 182 ( ) - Propeller Electrical De-Ice Boot Removal and Installation Manual (d) Hartzell Propeller Inc. Manual 183 ( ) - Propeller Anti-Icing Boot Removal and Installation Manual (14) Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by the applicable TC or STC holder s Instructions for Continued Airworthiness (ICA). C. Continued Airworthiness (1) Operators are urged to stay informed of Airworthiness information using Hartzell Propeller Inc. Service Bulletins and Service Letters that are available from Hartzell Propeller Inc. distributors, or from the Hartzell Propeller Inc. factory by subscription. Selected information is also available on the Hartzell Propeller Inc. website at INTRODUCTION Page 1-8 Rev. 21 Mar/15

45 D. Propeller Critical Parts Propeller Owner's Manual (1) The following maintenance procedures may involve propeller critical parts. These procedures have been substantiated based on Engineering analysis that expects this product will be operated and maintained using the procedures and inspections provided in the Instructions for Continued Airworthiness (ICA) for this product. Refer to the Illustrated Parts List chapter of the applicable maintenance manual for the applicable propeller model for the identification of specific Propeller Critical Parts. (2) Numerous propeller system parts can produce a propeller Major or Hazardous effect, even though those parts may not be considered as Propeller Critical Parts. The operating and maintenance procedures and inspections provided in the ICA for this product are, therefore, expected to be accomplished for all propeller system parts. INTRODUCTION Page 1-9 Rev. 21 Mar/15

46 6. Reference Publications A. Hartzell Propeller Inc. Publications NOTE: The following publications are referenced within this manual: Active Hartzell Propeller Inc. Service Bulletins, Service Letters, Service Instructions, and Service Advisories. Hartzell Propeller Inc. Manual No. 113B ( ) - Compact Non-Feathering (-1) and Aerobatic (-4) Propeller Overhaul and Maintenance Manual Hartzell Propeller Inc. Manual No. 117D ( ) - Compact Constant Speed and Feathering Propeller Overhaul and Maintenance Manual Hartzell Propeller Inc. Manual No. 127 ( ) - Metal Spinner Assembly Maintenance - Available on the Hartzell Propeller Inc. website at Hartzell Propeller Inc. Manual No. 130B ( ) - Mechanically Actuated Governor Maintenance Manual Hartzell Propeller Inc. Manual No. 133C ( ) - Aluminum Blade Overhaul Hartzell Propeller Inc. Manual No. 159 ( ) - Application Guide - Available on the Hartzell Propeller Inc. website at Hartzell Propeller Inc. Manual No. 165A ( ) - Illustrated Tool and Equipment Manual - Available on the Hartzell Propeller Inc. website at Hartzell Propeller Inc. Manual No. 173 ( ) - Composite Spinner Field Maintenance and Minor Repair Manual - Available on the Hartzell Propeller Inc. website at Hartzell Propeller Inc. Manual No. 180 ( ) - Propeller Ice Protection System Manual - Available on the Hartzell Propeller Inc. website at Hartzell Propeller Inc. Manual No. 181 ( ) - Propeller Ice Protection System Component Maintenance Manual - Available on the Hartzell Propeller Inc. website at www. hartzellprop.com INTRODUCTION Page 1-10 Rev. 21 Mar/15

47 Hartzell Propeller Inc. Manual No. 182 ( ) - Propeller Electrical De-ice Boot Removal and Installation Manual - Available on the Hartzell Propeller Inc. website at Hartzell Propeller Inc. Manual No. 183 ( ) - Propeller Anti-icing Boot Removal and Installation Manual - Available on the Hartzell Propeller Inc. website at Hartzell Propeller Inc. Manual No. 202A ( ) - Standard Practices Manual, Volumes 1 through 11 (Volume 7, Consumable Materials is available on the Hartzell Propeller Inc. website at Hartzell Propeller Inc. Service Letter HC-SL-61-61Y - Propeller - Overhaul Periods and Service Life Limits for Hartzell Propeller Inc. Aviation Components - Propellers, Governors, and Propeller Damper Assemblies - Available on the Hartzell Propeller Inc. website at INTRODUCTION Page 1-11 Rev. 21 Mar/15

48 B. References to Hartzell Propeller Inc. Publications NOTE: Specific Hartzell Propeller Inc. manuals and service documents are available on the Hartzell website at Refer to the section Required Publications in this chapter for the identification of these publications. (1) Special tooling is required for procedures throughout this manual. For further tooling information, refer to Hartzell Propeller Inc. Illustrated Tool and Equipment Manual 165A ( ). (a) Tooling references appear with the prefix TE directly following the tool name to which they apply. For example, a template which is reference number 133 will appear as: template TE133. (2) Consumable materials are referenced in certain sections throughout this manual. Specific approved materials are listed in the Consumable Materials chapter of Hartzell Propeller Inc. Standard Practices Manual 202A ( ). (a) The reference number for consumable materials appear with the prefix CM directly following the material to which they apply. For example, an approved adhesive that is reference number 16 will appear as: approved adhesive CM16. Only those items specified may be used. INTRODUCTION Page 1-12 Rev. 21 Mar/15

49 7. Definitions Propeller Owner's Manual A basic understanding of the following terms will assist in maintaining and operating Hartzell propeller systems. Term Definition Annealed Softening of material due to overexposure to heat. Blade Angle Measurement of blade airfoil location described as the angle between the blade airfoil and the surface described by propeller rotation. Brinelling A depression caused by failure of the material in compression. Chord A straight line between the leading and trailing edges of an airfoil. Cold Rolling Compressive rolling process for the retention area of single shoulder blades which provides improved strength and resistance to fatigue. Constant Force A force which is always present in some degree when the propeller is operating. Constant Speed A propeller system which employs a governing device to maintain a selected engine RPM. Corrosion Gradual material removal or deterioration due to chemical action. Crack Irregularly shaped separation within a material, sometimes visible as a narrow opening at the surface. Depression Surface area where the material has been compressed but not removed. Distortion Alteration of the original shape or size of a component. INTRODUCTION Page 1-13 Rev. 21 Mar/15

50 Term Propeller Owner's Manual Erosion Gradual wearing away or deterioration due to action of the elements. Exposure Material open to action of the elements. Feathering A propeller with blades that may be positioned parallel to the relative wind, thus reducing aerodynamic drag. Gouge Surface area where material has been removed Hazardous Propeller Definition Effect The hazardous propeller effects are defined in Title 14 CFR section 35.15(g)(1). Horizontal Balance.... Balance between the blade tip and the center of the hub. Impact Damage Damage that occurs when the propeller blade or hub assembly strikes, or is struck by, an object while in flight or on the ground. Major Propeller Effect. The major propeller effects are defined in Title 14 CFR section 35.15(g)(2). Nick Removal of paint and possibly a small amount of material. Onspeed Condition in which the RPM selected by the pilot through the propeller control lever and the actual engine (propeller) RPM are equal. Overhaul The periodic disassembly, inspection, repair, refinish, and reassembly of a propeller assembly to maintain airworthiness. INTRODUCTION Page 1-14 Rev. 21 Mar/15

51 Term Definition Overspeed Condition in which the RPM of the propeller or engine exceeds predetermined maximum limits; the condition in which the engine (propeller) RPM is higher than the RPM selected by the pilot through the propeller control lever. Overspeed Damage... Damage that occurs when the propeller hub assembly rotates at a speed greater than the maximum limit for which it is designed. Pitch Same as Blade Angle. Pitting Formation of a number of small, irregularly shaped cavities in surface material caused by corrosion or wear. Propeller Critical Part.. A part on the propeller whose primary failure can result in a hazardous propeller effect, as determined by the safety analysis required by Title 14 CFR section Scratch See Nick. Single Acting Hydraulically actuated propeller which utilizes a single oil supply for pitch control. Synchronizing Adjusting the RPM of all the propellers of a multi-engine aircraft to the same RPM. Synchrophasing A form of propeller sychronization in which not only the RPM of the engines (propellers) are held constant, but also the position of the propellers in relation to each other. INTRODUCTION Page 1-15 Rev. 21 Mar/15

52 Abbreviation Term Track In an assembled propeller, a measurement of the location of the blade tip with respect to the plane of rotation, used to verify face alignment and to compare blade tip location with respect to the locations of the other blades in the assembly. Underspeed The condition in which the actual engine (propeller) RPM is lower than the RPM selected by the pilot through the propeller control lever. Variable Force A force which may be applied, varied, or removed during propeller operation. Vertical Balance Balance between the leading and trailing edges of a two-blade propeller with the blades positioned vertically. Windmilling The rotation of an aircraft propeller caused by air flowing through it while the engine is not producing power. INTRODUCTION Page 1-16 Rev. 21 Mar/15

53 8. Abbreviations Abbreviation Term AMM Aircraft Maintenance Manual AN Air Force-Navy (or Army-Navy) AOG Aircraft on Ground FAA Federal Aviation Administration Ft-Lb Foot-Pound ICA Instructions for Continued Airworthiness ID Inside Diameter In-Lb Inch-Pound IPS Inches Per Second kpa Kilopascals Lbs Pounds MIL-X-XXX Military Specification MPI Major Periodic Inspection MS Military Standard MSDS Material Safety Data Sheet NAS National Aerospace Standards NASM National Aerospace Standards, Military N m Newton-Meters OD Outside Diameter POH Pilot s Operating handbook PSI Pounds per Square Inch RPM Revolutions per Minute STC Supplemental Type Certificate TBO Time Between Overhaul TC Type Certificate TSN Time Since New TSO Time Since Overhaul NOTE: TSN/TSO is considered as the time accumulated between rotation and landing, i.e., flight time. INTRODUCTION Page 1-17 Rev. 21 Mar/15

54 9. Hartzell Propeller Inc. Product Support Propeller Owner's Manual Hartzell Propeller is ready to assist you with questions concerning your propeller system. Hartzell Propeller Inc. Product Support may be reached during business hours (8:00 am through 5:00 pm, United States Eastern Time) at (937) or at (800) , toll free from the United States and Canada. Hartzell Propeller Inc. Product Support can also be reached by fax at (937) , and by at After business hours, you may leave a message on our 24 hour product support line at (937) or at (800) , toll free from the United States and Canada. A technical representative will contact you during normal business hours. Urgent AOG support is also available 24 hours per day, seven days per week via this message service. Additional information is available on our website at NOTE: When calling from outside the United States, dial (001) before dialing the above telephone numbers. 10. Warranty Service If you believe you have a warranty claim, it is necessary to contact Hartzell s Warranty Administrator. Hartzell s Warranty Administrator will provide a blank Warranty Application form. It is necessary to complete this form and return it to the Warranty Administrator for evaluation before proceeding with repair or inspection work. Upon receipt of this form, the Warranty Administrator will provide instructions on how to proceed. Hartzell Propeller Inc. Warranty may be reached during business hours (8:00 am. through 5:00 pm., United States Eastern Time) at (937) , or toll free from the United States and Canada at (800) Hartzell Propeller Inc. Warranty Administration can also be reached by fax, at (937) , or by at warranty@hartzellprop.com. NOTE: When calling from outside the United States, dial (001) before dialing the above telephone numbers. INTRODUCTION Page 1-18 Rev. 21 Mar/15

55 11. Hartzell Propeller Inc. Recommended Facilities A. Hartzell Propeller Inc. recommends using Hartzell approved distributors and repair facilities for the purchase, repair and overhaul of Hartzell Propeller Inc. propeller assemblies or components. B. Information about the Hartzell Propeller Inc. worldwide network of aftermarket distributors and approved repair facilites is available on the Hartzell Propeller Inc. website at INTRODUCTION Page 1-19 Rev. 21 Mar/15

56 (This page is intentionally blank.) INTRODUCTION Page 1-20 Rev. 21 Mar/15

57 DESCRIPTION AND OPERATION - CONTENTS 1. Description of Propeller and Systems A. System Overview Functional Description of Constant Speed Propeller Types A. Constant Speed, Non-Counterweighted Propellers ( )HC-( )( )Y( )-1( ) B. Constant Speed, Feathering Propellers ( )HC-( )( )Y( )-2( ) C. Constant Speed, Counterweighted (Aerobatic) Propellers ( )HC-( )( )Y( )-4( ) D. Constant Speed, Feathering, Turbine Propellers ( )HC-( )( )Y( )-5( ) Model Designation A. Aluminum Hub Propeller Model Identification B. Aluminum Blade Model Identification Governors A. Theory of Operation B. Governor Types C. Identification of Hartzell Propeller Inc. Governors Accumulator A. System Overview Propeller Ice Protection Systems A. Propeller Anti-ice System B. Propeller De-ice System DESCRIPTION AND OPERATION Page 2-1 Rev. 17 Jul/12

58 LIST OF FIGURES Cutaway of -1 Series Constant Speed, Non-Counterweighted Propeller ( )HC-( )( )Y( )-1( )... Figure Cutaway of -2 Series Constant Speed, Feathering Propeller ( )HC-( )( )Y( )-2... Figure Cutaway of -4 Series Constant Speed, Counterweighted (Aerobatic) Propeller ( )HC-( )( )Y( )-4( )... Figure Cutaway of -5 Series Constant Speed, Feathering Turbine Propeller ( )HC-( )( )Y( )-5( )... Figure Governor in Onspeed Condition... Figure Governor in Underspeed Condition... Figure Governor in Overspeed Condition... Figure Feathering Governor... Figure Synchronizer/Synchrophaser Governor... Figure Governor/Accumulator System... Figure DESCRIPTION AND OPERATION Page 2-2 Rev. 14 Jan/09

59 1. Description of Propeller and Systems A. System Overview Propeller Owner's Manual (1) The propellers covered in this manual are constant speed, single-acting, hydraulically actuated propellers. Some of the propellers have feathering capability. These propellers are designed primarily for use with reciprocating engines, but there are some turbine applications. (2) A constant speed propeller system is controlled by an engine speed sensing device (governor) to maintain a constant engine/propeller RPM by changing blade angle. (3) The governor uses an internal pump that is driven by the engine. This pump increases engine oil pressure for supply to the propeller. Engine speed sensing hardware within the governor controls the supply of oil to the propeller, supplying or draining oil as appropriate to maintain constant engine speed. (4) Propeller blade angle change is accomplished via a hydraulic piston/cylinder combination mounted on the forward end of the propeller hub. The linear motion of the hydraulic piston is transmitted to each blade through a pitch change rod and a fork. A pitch change knob, located at the base of each blade, is in contact with the fork. Each blade root is supported in the hub by a retention bearing. The retention bearing holds the blade firmly in the hub, but also allows the blade angle to change. (5) Propeller forces, consisting of: 1) mechanical spring action, 2) cylinder air charge, 3) counterweights, 4) and centrifugal twisting moment on the blades, in a variety of combinations, are constantly present while the propeller is operating. The summation of these forces is opposed by a variable hydraulic force (oil pressure from the engine driven governor). Oil pressure is metered by the governor to oppose this constant force. The propeller forces, opposed by the variable hydraulic force cause the propeller blade angle to increase, decrease, or maintain current setting. DESCRIPTION AND OPERATION Page 2-3 Rev. 13 Aug/06

60 SPINNER ADAPTER (IF REQUIRED) BLADE BLADE RETENTION BEARING HUB APS6164 SPRING ENGINE FLANGE PISTON MOUNTING STUD (K OR R FLANGE SHOWN) OIL SHAFT O-RING CYLINDER (OIL PRESSURE TO INCREASE BLADE ANGLE AND REDUCE RPM) STARTER GEAR (LYCOMING ENGINE) LOW PITCH STOP SPINNER DOME PITCH CHANGE ROD FORK LUBRICATION FITTING BALANCE WEIGHTS Cutaway of -1 Series Constant Speed, Non-Counterweighted Propeller ( )HC-( )( )Y( )-1( ) Figure 2-1 DESCRIPTION AND OPERATION Page 2-4 Rev. 13 Aug/06

61 (6) Oil under pressure from the engine-driven governor is supplied to the hydraulic cylinder through the pitch change rod. Increasing or decreasing the oil volume within the hydraulic cylinder either increases blade angle to reduce engine RPM, or reduces blade angle to increase engine RPM. By changing the blade angle, the governor maintains constant engine RPM (within limits), independent of the throttle setting. (7) If oil pressure is lost at any time, the summation of propeller forces, which is in direct opposition to the lost variable hydraulic force, either increases or reduces blade angle, depending upon propeller model. 2. Functional Description of Constant Speed Propeller Types A. Constant Speed, Non-Counterweighted Propellers ( )HC-( )( )Y( )-1( ) (1) Refer to Figure 2-1. The -1 Series propellers are constant speed, non-counterweighted propellers. The propellers are capable of blade angles between a low positive pitch (low pitch) and high positive pitch (high pitch). This model series is not equipped with an air charge and does not feather. (2) Centrifugal twisting moment acting on the blades moves the blades to a low blade angle (low pitch) to increase RPM. Since the centrifugal twisting moment is only present when the propeller is rotating, a mechanical spring is installed within the propeller to assist movement of the blades to a lower pitch position as RPM decays, and to reduce the propeller pitch to the low pitch stop when the propeller is static. With the blades at low pitch, the load on the starter when starting the engine is reduced significantly. (3) Oil pressure opposes the spring and centrifugal twisting moment to move the blades to a high blade angle (high pitch), reducing engine RPM. (4) If oil pressure is lost at any time, the propeller will move to low pitch. This occurs because the spring and blade centrifugal twisting moment are no longer opposed by hydraulic oil pressure. The propeller will then reduce blade pitch to the low pitch stop. DESCRIPTION AND OPERATION Page 2-5 Rev. 13 Aug/06

62 BLADE APS6165 BLADE RETENTION BEARING HUB PITCH CHANGE ROD START LOCK LATCH SPINNER BULKHEAD OIL SPRING PISTON ENGINE FLANGE AIR CHARGE CYLINDER (OIL PRESSURE TO REDUCE BLADE ANGLE AND INCREASE RPM) SHAFT O-RING MOUNTING NUT (F FLANGE SHOWN) LOW PITCH STOP LUBRICATION FITTING FORK REMOVABLE SPINNER CAP BALANCE WEIGHTS COUNTERWEIGHT SPINNER DOME Cutaway of -2 Series Constant Speed, Feathering Propeller ( )HC-( )( )Y( )-2 Figure 2-2 DESCRIPTION AND OPERATION Page 2-6 Rev. 13 Aug/06

63 B. Constant Speed, Feathering Propellers ( )HC-( )( )Y( )-2 (1) Refer to Figure 2-2. The -2 Series propellers are constant speed propellers that use an air charge, spring, and counterweights (if installed) to move the blades to high pitch/feather position. Blade centrifugal twisting moment acts to move the blades to low pitch, but the air charge, spring, and counterweights overcome this force. Oil pressure against a propeller mounted hydraulic piston opposes the counterweight, spring, and air charge forces to move the blades to low blade angle (low pitch). (2) The action of the air charge, spring, and counterweights tends to move the blades to a higher blade angle (high pitch), reducing engine RPM. Oil pressure toward low pitch increases engine RPM. (3) If oil pressure is lost during operation, the propeller will feather. Feathering occurs because the air charge, spring, and blade counterweights are no longer opposed by hydraulic oil pressure. The air charge, spring and blade counterweights are then free to increase blade pitch to the feathering (high pitch) stop. (4) Normal in-flight feathering of these propellers is accomplished when the pilot retards the propeller pitch control past the feather detent. This allows control oil to drain from the cylinder and return to the engine sump. The engine can then be shut down. (5) Normal in-flight unfeathering is accomplished when the pilot positions the propeller pitch control into the normal flight (governing) range and an engine restart is attempted. (6) Some aircraft are equipped with a hydraulic accumulator, which stores a supply of oil under pressure. This oil supply is released to unfeather the propeller during an in-flight engine restart. Pressurized oil is directed to the propeller, resulting in blade angle decrease. The propeller begins to windmill, and engine restart is possible. DESCRIPTION AND OPERATION Page 2-7 Rev. 13 Aug/06

64 (7) When the engine is stopped on the ground, it is undesirable to feather the propeller, as the high blade angle inhibits engine starting. To prevent feathering during normal engine shutdown on the ground, the propeller incorporates spring energized latches. If propeller rotation is approximately 800 RPM or above, the latches are disengaged by centrifugal force acting on the latches to compress the springs. When RPM drops below 800 RPM (and blade angle is typically within 7 degrees of the low pitch stop), the springs overcome the latch weight centrifugal force and move the latches to engage the high pitch stops, preventing blade angle movement to feather during normal engine shutdown. DESCRIPTION AND OPERATION Page 2-8 Rev. 13 Aug/06

65 (This page is intentionally blank) DESCRIPTION AND OPERATION Page 2-9 Rev. 13 Aug/06

66 BLADE APS6147 BLADE RETENTION BEARING HUB PITCH CHANGE ROD SPINNER BULKHEAD OIL INTERNAL SPINNER SUPPORT ENGINE FLANGE PISTON MOUNTING STUD SHAFT O-RING (F FLANGE SHOWN) CYLINDER (OIL PRESSURE TO REDUCE BLADE ANGLE AND INCREASE RPM) UHMW TAPE LUBRICATION FITTING FORK LOW PITCH STOP BALANCE WEIGHTS COUNTERWEIGHT Cutaway of -4 Series Constant Speed, Counterweighted (Aerobatic) Propeller ( )HC-( )( )Y( )-4( ) Figure 2-3 DESCRIPTION AND OPERATION Page 2-10 Rev. 13 Aug/06

67 C. Constant Speed, Counterweighted (Aerobatic) Propellers ( )HC-( )( )Y( )-4( ) (1) Refer to Figure 2-3. The -4 Series propellers are constant speed propellers in which blade mounted counterweight forces act to move the blades to high pitch. This model series is not equipped with an air charge and does not feather. The blade centrifugal twisting moment acts to move the blades to low blade angle (low pitch), but the counterweights are large enough to neutralize this force and produce a net increase in blade angle. Oil pressure against a propeller mounted hydraulic piston opposes the counterweight forces to move the blades to low pitch. (2) The action of the counterweights tends to move the blades to a high blade angle (high pitch), reducing engine RPM. Oil pressure toward low pitch increases engine RPM. (3) If oil pressure is lost at any time, the propeller will move to high pitch to avoid overspeeding. Movement to high pitch occurs because the blade counterweights are no longer opposed by hydraulic oil pressure. The blade counterweights are then free to increase blade pitch toward the high pitch stop. DESCRIPTION AND OPERATION Page 2-11 Rev. 13 Aug/06

68 BLADE APS6148 SPINNER DOME BLADE RETENTION BEARING SPINNER BULKHEAD COUNTERWEIGHT START LOCK LATCH OIL PISTON SPRING REMOVABLE SPINNER CAP SHAFT O-RING (N FLANGE SHOWN) LOW PITCH STOP PITCH CHANGE ROD MOUNTING NUT ENGINE FLANGE FORK HUB AIR CHARGE CYLINDER (OIL PRESSURE TO REDUCE BLADE ANGLE AND INCREASE RPM) Cutaway of -5 Series Constant Speed, Feathering, Turbine Propeller ( )HC-( )( )Y( )-5( ) Figure 2-4 DESCRIPTION AND OPERATION Page 2-12 Rev. 13 Aug/06

69 D. Constant Speed, Feathering, Turbine Propellers ( )HC-( )( )Y( )-5( ) (1) Refer to Figure 2-4. The -5 Series propellers are constant speed propellers that use an air charge, spring, and blade mounted counterweights to move the blades to high pitch/ feather position. Blade centrifugal twisting moment acts to move the blades to low pitch, but the air charge, spring, and counterweights overcome this force. Oil pressure against a propeller mounted hydraulic piston opposes the counterweight, spring, and air charge forces to move the blades to low blade angle (low pitch). (2) The action of the air charge, spring, and counterweights tends to move the blades to a higher blade angle (high pitch), reducing engine RPM. Oil pressure toward low pitch increases engine RPM. (3) If oil pressure is lost during operation, the propeller will feather. Feathering occurs because the air charge, spring, and counterweights are no longer opposed by hydraulic oil pressure. The air charge, spring, and blade counterweights are then free to increase blade pitch to the feathering (high pitch) stop. (4) Normal in-flight feathering of these propellers is accomplished when the pilot retards the propeller pitch control past the feather detent. This allows control oil to drain from the cylinder and return to the engine sump. The engine may then be shut down. (5) Normal in-flight unfeathering occurs when the pilot positions the propeller pitch control into the normal flight (governing) range and restarts the engine. As engine speed increases, oil is directed to the propeller, and blade angle decreases. DESCRIPTION AND OPERATION Page 2-13 Rev. 14 Jan/09

70 (6) In some cases, particularly in seaplane applications, it is undesirable to feather the propeller when the engine is stopped after landing. To prevent feathering during normal engine shutdown, the propeller incorporates spring energized latches. If propeller rotation is approximately 800 RPM or above, the latches are disengaged by centrifugal force acting on the latch weights to compress the springs. When RPM drops below 800 RPM (and blade angle is typically within 7 degrees of the low pitch stop), the springs overcome the centrifugal force and move the latches to engage the high pitch stops, preventing blade angle movement to feather. (7) Start lock latches are not employed on all -5 propellers. Propellers without start lock latches will feather during normal engine shutdown. DESCRIPTION AND OPERATION Page 2-14 Rev. 13 Aug/06

71 (This page is intentionally blank) DESCRIPTION AND OPERATION Page 2-15 Rev. 7 Oct/02

72 3. Model Designation The following pages illustrate sample model designations for Hartzell Propeller Inc. compact propeller hubs and blades. A. Aluminum Hub Propeller Model Identification B HC - C 2 Y F - 1 BF SEE NEXT PAGE HUB MTG BOLT DOWELS NO. OF BOLTS TYP. ENGINE FLANGE CIRCLE NO. DIA. OR STUDS D 4.00 in. N/A N/A 8 (1/2") CONT. F 4.00 in. 2 1/2 6 (1/2") CONT. L 4.75 in. N/A N/A 6 (7/16") LYC. K 4.75 in. N/A N/A 6 (1/2") LYC, R 4.75 in. N/A N/A 6 (1/2") LYC N 4.25 in. 2 1/2 8 (9/16") GTSI0520 BLADE SHANK Or RETENTION SYSTEM Y SHANK, ALUMINUM BLADE, INTEGRAL PITCH CHANGE ARM NO. OF BLADES 2, 3, 4 BASIC DESIGN CHARACTERISTIC FLANGE DISTANCE FROM HUB DESIGNATION PARTING LINE TO FLANGE FACE C - STANDARD HUB F K,R,L (HC-C4YR-( ) N E - EXTENDED HUB F,K,R,L N F - EXTENDED HUB R,L G - EXTENDED HUB F R H - EXTENDED HUB F,N I - EXTENDED HUB R F J - EXTENDED HUB F L - EXTENDED HUB F M - EXTENDED HUB R HC FLANGE ANGULAR INDEX HARTZELL CONTROLLABLE with respect to # 1 blade, viewed clockwise facing propeller flange: PREFIX ANGULAR INDEX CLOCKING FEATURE FLANGE BLANK - 90 AND 270 DEGREES DOWEL PINS F, N BLANK 0 AND 180 DEGREES NON-COUNTER BORED K, R, L HOLES B - 30 AND 210 DEGREES DOWEL PINS F B AND 300 DEGREES NON-COUNTER BORED K, R HOLES C AND 330 DEGREES DOWEL PINS F D - 60 AND 240 DEGREES NON-COUNTER BORED K, R HOLES D - 60 AND 240 DEGREES DOWEL PINS F E, P 0 AND 180 DEGREES DOWEL PINS F, D DESCRIPTION AND OPERATION Page 2-16 Rev. 22 Jul/16

73 Aluminum Hub Propeller Model Identification B HC - C 2 Y F - 1 BF MINOR MODIFICATIONS (up to 5 characters) -1 PROPS A - C2YF: DIFFERENT SPINNER MOUNTING PARTS; C2YK: DIFFERENT P.C.ROD, FORK A - F3YR-1: INTEGRAL HUB EXTENSION (NO "A": BOLT ON EXTENSION) B - 2 BLADE: DIFFERENT CYLINDER, P.C.ROD, SPRING, LOW PITCH STOP C - BHC-J2YF-1C: COMPOSITE BLADE D - A SPINNER MOUNTING KIT E - C4YF: B-2984 SPACER with B-1738 STUDS F - LARGE PITCH CHANGE KNOB, FORK H - A SPINNER MOUNTING KIT L - LEFT HAND ROTATION M - 3 BLADE: DIFFERENT CYLINDER, P.C. ROD, SPRING, LOW PITCH STOP P - 2 BLADE: HUB WITH A B-SUFFIX SERIAL NUMBER R - 3 BLADE: LARGE CYLINDER AND PISTON J - LEFT HAND TRACTOR S - HUB EXTENSION -2 PROPS - SEE NEXT PAGE -4 PROPS A - 2 BLADE: A SPINNER KIT (attaches to hub) B - 2 BLADE: -2 CYLINDER, LOW STOP SCREW B - 3 BLADE: -2 CYLINDER, LOW STOP SCREW C - 2 BLADE: -2 CYLINDER, LOW STOP SCREW, F - LARGE PITCH CHANGE KNOB, FORK L - LEFT HAND ROTATION P - 2 BLADE: HUB WITH A B-SUFFIX SERIAL NUMBER -5 PROPS A - C3YN: START LOCKS F - C3YF: NO START LOCKS SPECIFIC DESIGN FEATURES 1 - CONSTANT SPEED, NO COUNTERWEIGHT OIL PRESSURE TO HIGH PITCH, BLADE CENTRIFUGAL FORCE TO LOW 2 - CONSTANT SPEED, FEATHERING, OIL PRESSURE TO LOW PITCH, AIR CHARGE AND SPRING TO HIGH PITCH/FEATHER (some exceptions), MAY OR MAY NOT HAVE COUNTERWEIGHTS TO HIGH PITCH/FEATHER 4 - CONSTANT SPEED, OIL PRESSURE TO LOW PITCH, COUNTERWEIGHTS TO HIGH PITCH 5 - CONSTANT SPEED, FEATHERING, OIL PRESSURE TO LOW PITCH, AIR CHARGE, SPRING, AND COUNTERWEIGHTS TO HIGH PITCH/ FEATHER (EXCEPT SOLOY PROP, SAME AS -2 EXCEPT TURBINE O-RING) DESCRIPTION AND OPERATION Page 2-17 Rev. 12 Apr/05

74 Aluminum Hub Propeller Model Identification -2 PROPS: B HC - C 2 Y F - 1 BF MINOR MODIFICATIONS, up to five characters ( )HC-(C,I,L,M )2Y(F,K,L,R )-2 PROPS B STOP UNITS C - COUNTERWEIGHTS, STOP UNITS D - A SPINNER MOUNTING KIT E - A SPINNER MOUNTING KIT F - LARGE PITCH CHANGE KNOB, FORK G - DAMPER INSTALLED & A SPINNER MTG KIT H - A SPINNER MOUNTING KIT K - SPECIAL AIR CHARGE DECAL, -3 MOUNTING STUDS L - LEFT HAND ROTATION P - HUB WITH A B-SUFFIX SERIAL NUMBER R - 2 & 3 BLADE: LARGE DIA. CYLINDER AND PISTON ( )HC-(C,I,L,M )2Y(F,K,L,R )-2C_U_ PROPS C - COUNTERWEIGHTS D - A SPINNER MOUNTING KIT E - A SPINNER MOUNTING KIT F - LARGE PITCH CHANGE KNOB, FORK G - DAMPER INSTALLED & A SPINNER MTG KIT H - A SPINNER MOUNTING KIT K - SPECIAL AIR CHARGE DECAL, -3 MOUNTING STUDS L - LEFT HAND ROTATION P - HUB WITH A B-SUFFIX SERIAL NUMBER U - FEATHER ASSIST SPRING KIT IN CYLINDER HC-E2Y(R,K,L)-2(R)B( ) PROPS B STOP UNITS (non-counterweighted props) F - LARGE PITCH CHANGE KNOB, FORK L - LEFT HAND ROTATION P - HUB WITH A B-SUFFIX SERIAL NUMBER R - 2 & 3 BLADE: LARGE DIA. CYLINDER AND PISTON S - A-2273 SPRING ASSY. IN HUB EXTENSION T - B-1586 SPRING ASSY. IN HUB EXTENSION U - FEATHER ASSIST SPRING KIT IN CYLINDER HC-(E,F)2Y(R,L)-2 PROPS A - F3YR-2: INTEGRAL HUB EXTENSION (NO "A": BOLT ON EXTENSION) F - LARGE PITCH CHANGE KNOB, FORK L - LEFT HAND ROTATION P - HUB WITH A B-SUFFIX SERIAL NUMBER T - B-1586 SPRING ASSY. IN HUB EXTENSION U - B-1589/ SPRING ASSY. IN CYLINDER BHC-J2YF-2C PROPS C - COUNTERWEIGHTS F - LARGE PITCH CHANGE KNOB, FORK P - HUB WITH A B-SUFFIX SERIAL NUMBER U - B-1589/ SPRING ASSY. IN CYLINDER HC-F3YR-2 PROPS F - LARGE PITCH CHANGE KNOB, FORK H - INCLUDES A HIGH PITCH STOP U - B-1589/ SPRING ASSY. IN CYLINDER DESCRIPTION AND OPERATION Page 2-18 Rev. 15 Jul/09

75 Aluminum Hub Propeller Model Identification -2 PROPS CONTINUED: B HC - C 2 Y F - 1 BF MINOR MODIFICATIONS, up to five characters (P)HC-(E,J,H)3Y(R,N,F)-2 PROPS A - E3YR-2: INTEGRAL HUB EXT. (no A, bolt-on extension) F - LARGE PITCH CHANGE KNOB, FORK L - LEFT HAND ROTATION T - B-1586 SPRING ASSY. IN HUB EXTENSION U - B-1589/ SPRING ASSY. IN CYLINDER (P,E)HC-(C,G,I)3Y(R,N,F)-2 PROPS A - C3YN-2L: DIFFERENT SPINNER MOUNTING KIT D - C3YN-2: DIFFERENT SPINNER INSTALLATION KIT/ASSY. E - C3YR-2: DIFFERENT SPINNER, B-1106 SPRING ASSY. USABLE F - LARGE PITCH CHANGE KNOB, FORK K - C3YF-2: DIFFERENT SPINNER, MOUNTING STUDS L - LEFT HAND ROTATION U - B-1589/ SPRING ASSY. IN CYLINDER HC-C4Y(R,F,N)-2 PROPS E - LONG STUDS WITH HUB EXTENSION L - LEFT HAND ROTATION DESCRIPTION AND OPERATION Page 2-19 Rev. 12 Apr/05

76 B. Aluminum Blade Model Identification Hartzell Propeller Inc. uses a model designation to identify specific propeller and blade assemblies. Example: HC-C3YR-1RF/F8468A-6R. A slash mark separates the propeller and blade designations. The propeller model designation is impression stamped on the propeller hub. The blade designation is impression stamped on the blade butt end (internal) and is either on a label or ink stamped on the blade camber side (external). prop model/f 8475 A-3R Dash Number: change from basic propeller diameter. In this example, the nominal 84 inch diameter has been reduced 3 inches = 81 inch diameter (with some exceptions) there may be a letter following the dash number. (Note: This basic diameter may not reflect the actual prop diameter, depending on the hub model used.) A - slightly thinner and narrower tip fairing E - elliptical tip Q - Q-tip, factory 90 degree bent tip R - specifically rounded tip S - square tip T - specifically rounded tip Suffix letters: A - dimensional change to basic blade or Y shank pitch knob location B - anti-icing or de-ice boot C - modified blade, dimensional or blade twist modification from initial blade design D - modified blade, blade twist or thickness change E - de-ice boot, elliptical tip, or alternate life limit F - modified blade, dimensional modification (width/thickness) H - hard alloy (7076) K - de-ice boot N - shank modification (pilot tube hole), thickness added to certain blade shanks Q - Q-tip, factory 90 degree formed tip R - specifically rounded tips S - shot peening of blade surface, or square tip (Exception: Blade model M10476 was manufactured with a shot peened surface; however, the "S" shot peen designator was not included in the model number. The "S" designator will be added to M10476 blades at overhaul.) T - twist blank - original design, no changes other letters - location of pitch change knob (Y shank), twist The first 2 or 3 numbers indicate basic design diameter (in inches), the last 2 numbers indicate a specific model Prefix of up to 3 letters: C - counterweighted Y shank F - large pitch change knob Y shank H - right hand rotation, pusher J - left hand rotation, tractor L - left hand rotation, pusher D,E,M,MV,P,R,T,V,W - shank design blank - standard blade, right hand rotation, tractor (X,Y, and Z shanks + few others) DESCRIPTION AND OPERATION Page 2-20 Rev. 22 Jul/16

77 (This page is intentionally blank.) DESCRIPTION AND OPERATION Page 2-21 Rev. 16 Oct/09

78 APS6149 Propeller RPM Control Flyweights Centrifugal Force Speeder Spring Centrifugal Force Pilot Valve Governor in Onspeed Condition Figure 2-5 Propeller RPM Control APS6150 Flyweights Centrifugal Force Speeder Spring Centrifugal Force Pilot Valve Governor in Underspeed Condition Figure 2-6 Propeller RPM Control APS6151 Flyweights Centrifugal Force Speeder Spring Centrifugal Force Pilot Valve Governor in Overspeed Condition Figure 2-7 DESCRIPTION AND OPERATION Page 2-22 Rev. 16 Oct/09

79 4. Governors A. Theory of Operation Propeller Owner's Manual (1) A governor is an engine RPM sensing device and high pressure oil pump. In a constant speed propeller system, the governor responds to a change in engine RPM by directing oil under pressure to the propeller hydraulic cylinder or by releasing oil from the hydraulic cylinder. The change in oil volume in the hydraulic cylinder changes the blade angle and maintains the propeller system RPM. The governor is set for a specific RPM via the cockpit propeller control, which compresses or releases the governor speeder spring. (2) When the engine is operating at the RPM set by the pilot using the cockpit control, the governor is operating onspeed. Refer to Figure 2-5. In an onspeed condition, the centrifugal force acting on the flyweights is balanced by the speeder spring, and the pilot valve is neither directing oil to nor from the propeller hydraulic cylinder. (3) When the engine is operating below the RPM set by the pilot using the cockpit control, the governor is operating underspeed. Refer to Figure 2-6. In an underspeed condition, the flyweights tilt inward because there is not enough centrifugal force on the flyweights to overcome the force of the speeder spring. The pilot valve, forced down by the speeder spring, meters oil flow to decrease propeller pitch and raise engine RPM. (4) When the engine is operating above the RPM set by the pilot using the cockpit control, the governor is operating overspeed. Refer to Figure 2-7. In an overspeed condition, the centrifugal force acting on the flyweights is greater than the speeder spring force. The flyweights tilt outward, and raise the pilot valve. The pilot valve then meters oil flow to increase propeller pitch and lower engine RPM. DESCRIPTION AND OPERATION Page 2-23 Rev. 12 Apr/05

80 Propeller RPM Control Lift Rod Flyweights Speeder Spring Pilot Valve APS6152A Feathering Governor Figure 2-8 Propeller RPM Control Coil Lift Rod Flyweights Speeder Spring APS6153A Pilot Valve Synchronizer/Synchrophaser Governor Figure 2-9 DESCRIPTION AND OPERATION Page 2-24 Rev. 16 Oct/09

81 (5) Refer to Figure 2-8. This figure illustrates a feathering propeller governor. This governor is similar to the constant speed governors illustrated in Figures 205 through 207 with the addition of the lift rod. When it is desired to feather the propeller, the lift rod may be moved by the cockpit control to mechanically engage the pilot valve to lift the valve. The lifted pilot valve dumps oil to increase propeller pitch until the propeller feathers. (6) Refer to Figure 2-9. This figure illustrates a governor as a component of a synchronizing or synchrophasing system. A synchronizing system is employed in a multi-engine aircraft to keep the engines operating at the same RPM. A synchrophasing system not only keeps RPM of the engines consistent, but also keeps the propeller blades operating in phase with each other. Both synchronizing and synchrophasing systems serve to reduce noise and vibration. (7) A Hartzell Propeller Inc. synchronizing or synchrophasing system uses one engine (the master engine) as an RPM and phase reference and adjusts the RPM of the remaining engine(s) [slave engine(s)] to match it. The RPM of the master engine is monitored electronically, and this information is used to adjust the voltage applied to the electrical coil on the slave governor(s). The voltage to the coil either raises or lowers a rod which changes the force on the speeder spring. In this manner, engine RPM and phase of the propellers is synchronized or synchrophased. DESCRIPTION AND OPERATION Page 2-25 Rev. 17 Jul/12

82 B. Governor Types Propeller Owner's Manual The governors commonly used in Hartzell Propeller Inc. Compact Constant Speed propeller systems are supplied either by Hartzell or several other manufacturers. These governor types function in a similar manner. C. Identification of Hartzell Propeller Inc. Governors A Hartzell governor may be identified by its model number as follows: Ex. F-6-4. (X) - (X) - (X) Minor variation of basic design. (Numeric and/or alpha character) Specific model application (numeric character) - special attributes Basic Body and Major Parts Modification (alpha character) NOTE: Refer to Hartzell Propeller Inc. Manual 130B ( ) for maintenance and overhaul instructions for Hartzell Propeller Inc. governors. DESCRIPTION AND OPERATION Page 2-26 Rev. 17 Jul/12

83 (This page is intentionally blank.) DESCRIPTION AND OPERATION Page 2-27 Rev. 14 Jan/09

84 TI Propeller Control Oil Propeller Oil Drain Engine Oil Governor Governor/Accumulator System Figure 2-10 Engine Charge Valve Accumulator Air or Nitrogen Piston Oil Governor To Accumulator Connection DESCRIPTION AND OPERATION Page 2-28 Rev. 14 Jan/09

85 5. Accumulator A. System Overview Propeller Owner's Manual (1) An unfeathering accumulator is a device that stores a volume of oil at a pressure and supplies it to the propeller, when commanded by the pilot/governor, to move the propeller piston and the connected blades to a lower blade angle for the purpose of starting the associated engine. Lower blade angles will cause the propeller to windmill and make the engine easier to start. (2) Hartzell Propeller Inc. manufactures an accumulator that is a cylinder with a moveable internal piston. One end of the cylinder and piston is filled with engine oil through a fitting, and the other end of the cylinder and piston is filled with air or nitrogen to a pressure through an air valve. The accumulator is a self contained unit and is usually installed at some remote location in the engine compartment. An oil supply hose is connected between the accumulator and the governor. (3) The governor has a fitting or threaded hole to attach with an oil supply hose that is connected to the accumulator on the other end. During operation of the engine and propeller, the governor supplies oil to the accumulator and maintains oil in the accumulator during engine operation. (4) The pilot commands feather of the propeller by moving the RPM control of the governor toward lower RPM to reach the feather command location. The governor disconnects the oil supply to the accumulator and seals a volume of oil under pressure in the accumulator. The governor then connects the oil supply line between governor and propeller to drain oil from the propeller piston and permit the propeller blades to move to a feather stop in the propeller. DESCRIPTION AND OPERATION Page 2-29 Rev. 17 Jul/12

86 (5) Unfeathering occurs when the governor RPM control is moved by the pilot from the feather location to a higher RPM selection for governing. The governor disconnects the propeller oil supply from drain and reconnects it to the governed oil supply line from the governor. At that point there is no oil available from the engine oil pump to the governor; therefore, no governed oil is available from the governor for controlling the propeller blade angle and RPM. Further movement of the governor RPM control toward higher RPM will cause the governor to connect the accumulator to the oil supply line from governor to the propeller. The air or nitrogen pressure in one side of the accumulator will push a piston to force oil from the other side of the accumulator through the governor to the propeller piston to move the propeller blades from feather to a lower blade angle. The propeller will then begin to windmill and will permit the engine to start. (6) Hartzell Propeller Inc. manufacturers governors that have unfeathering and feathering capability, although governors that are able to feather a propeller are not automatically capable of unfeathering the propeller. DESCRIPTION AND OPERATION Page 2-30 Rev. 17 Jul/12

87 6. Propeller Ice Protection Systems Propeller Owner's Manual Some Hartzell Propeller Inc. compact propellers may be equipped with an anti-ice or a de-ice system. A short description of each of these systems follows: A. Propeller Anti-ice System A propeller anti-ice system is a system that prevents ice from forming on propeller surfaces. The system dispenses a liquid (usually isopropyl alcohol) which mixes with moisture on the propeller blades, reducing the freezing point of the water. This water/alcohol mixture flows off the blades before ice forms. This system must be in use before ice forms. It is ineffective in removing ice that has already formed. (1) System Overview (a) A typical anti-ice system consists of a fluid tank, pump, and distribution tubing. (b) The rate at which the anti-icing fluid is dispensed is controlled by a pump speed rheostat in the cockpit. (c) The anti-icing fluid is dispensed through airframe mounted distribution tubing and into a rotating slinger ring mounted on the rear of the propeller hub. The anti-icing fluid is then directed through blade feed tubes from the slinger ring onto the blades via centrifugal force. The anti-icing fluid is directed onto anti-icing boots that are attached to the leading edge of the blade. These anti-icing boots evenly distribute and direct the fluid along the blade leading edge. DESCRIPTION AND OPERATION Page 2-31 Rev. 17 Jul/12

88 B. Propeller De-ice System Propeller Owner's Manual A propeller de-ice system is a system that allows ice to form, and then removes it by electrically heating the de-ice boots. The ice partially melts and is thrown from the blade by centrifugal force. (1) System Overview (a) A de-ice system consists of one or more on/off switches, a timer or cycling unit, a slip ring, brush blocks, and de-ice boots. The pilot controls the operation of the de-ice system by turning on one or more switches. All de-ice systems have a master switch, and may have another toggle switch for each propeller. Some systems also have a selector switch to adjust for light or heavy icing conditions. (b) The timer or cycling unit determines the sequence of which blades (or portion thereof) are currently being de-iced, and for what length of time. The cycling unit applies power to each de-ice boot or boot segment in a sequential order. (c) A brush block, which is normally mounted on the engine just behind the propeller, is used to transfer electricity to the slip ring. The slip ring rotates with the propeller, and provides a current path to the blade de-ice boots. (d) De-ice boots contain internal heating elements. These boots are securely attached to the leading edges of each blade with adhesive. DESCRIPTION AND OPERATION Page 2-32 Rev. 12 Apr/05

89 INSTALLATION AND REMOVAL - CONTENTS 1. Tools, Consumables, and Expendables A. Tooling B. Consumables C. Expendables Pre-Installation A. Inspection of Shipping Package B. Uncrating C. Inspection after Shipment D. Reassembly of a Propeller Disassembled for Shipment E. Air Charge Pressure Check (-2 and -5 Propellers) Spinner Pre-Installation A. General B. Installation of a Metal Spinner Bulkhead on the Propeller Hub C. Installation of a Composite Spinner Bulkhead on a Propeller Hub - Refer to Table 3-3 and Figure D. Spinner Adapter to Starter Ring Gear Installation Propeller Installation A. Flange Description B. Installation of D Flange Propellers C. Installation of F Flange Propellers D. Installation of N Flange Propellers E. Installation of L Flange Propellers, Except Model HC-E2YL-( ) F. Installation of HC-E2YL-( ) Propellers G. Installation of K and R Flange Propellers Damper Installation A. Installation of C-1576 Damper (Hartzell Propeller Inc. Kit A-1583) Spinner Installation A. Installing a One-Piece Spinner Dome, Except Spinner Assembly C-3567-(4,8) With a D (P) Spinner Dome B. Installing Spinner Assembly C-3567-(4,8) With a D (P) Spinner Dome C. Installing a Two-Piece Spinner Dome (Procedure 1) D. Installing a Two-Piece Spinner Dome (Procedure 2) INSTALLATION AND REMOVAL Page 3-1 Rev. 21 Mar/15

90 INSTALLATION AND REMOVAL - CONTENTS, CONTINUED 7. Post-Installation Checks Spinner Removal A. Removal of One-Piece Spinner B. Removal of Two-Piece Spinner C. Hub Mounted Spinner Bulkhead Removal D. Starter Ring Gear Spinner Adapter Removal Propeller Removal A. Removal of D Flange Propellers B. Removal of F Flange Propellers C. Removal of N Flange Propellers D. Removal of L Flange Propellers, Except Model HC-E2YL-( ) E. Removal of HC-E2YL-( ) Propellers F. Removal of K and R Flange Propellers INSTALLATION AND REMOVAL Page 3-2 Rev. 21 Mar/15

91 LIST OF FIGURES Determining Torque Value When Using Torquing Adapter... Figure Diagram of Torquing Sequence for Propeller Mounting Hardware... Figure Hub Clamping Bolt Location... Figure Metal Spinner Bulkhead and Spinner Mounting (Hub Mounted Spinner)... Figure Composite Bulkhead and Spinner Mounting (Hub Mounted Spinner)... Figure Spinner Adapter and Spinner Mounting (Starter Ring Gear Mount)... Figure D Flange Propeller Mounting... Figure F and N Flange Propeller Mounting... Figure L, K, and R Flange Propeller Mounting... Figure Damper Installation... Figure Installing the Spacer Base and Spinner Mounting Spacers... Figure Install the Plastic Forward Bulkhead and Pre-fit the Spinner Dome...Figure Optional Tape on the Forward Bulkhead...Figure Spinner Dome Mounting Hole Alignment... Figure Two-Piece Spinner Mounting (Procedure 1).. Figure Two-Piece Spinner Mounting (Procedure 2).. Figure Spinner Dome to Bulkhead Mounting Hole Alignment...Figure INSTALLATION AND REMOVAL Page 3-3 Rev. 22 Jul/16

92 LIST OF TABLES Torque Table... Table Metal Spinner Bulkhead Mounting Hardware... Table Composite Spinner Bulkhead Mounting Hardware... Table Propeller/Engine Flange O-rings and Mounting Hardware... Table Spinner Dome and Spinner Cap Mounting Hardware... Table INSTALLATION AND REMOVAL Page 3-4 Rev. 21 Mar/15

93 1. Tools, Consumables, and Expendables The following tools, consumables, and expendables will be required for propeller removal or installation: NOTE: Compact propellers are manufactured with six basic hub mounting flange designs. The flange types are D, F, K, L, N, or R. The flange type used on a particular propeller installation is indicated in the propeller model number stamped on the hub. For example, HC-C2YF-4A indicates an F flange. Refer to Aluminum Hub Propeller Model Identification in the Description and Operation chapter of this manual for a description of each flange. A. Tooling CAUTION: USE CARE WHEN USING TOOLS. INCORRECT USE OF TOOLS COULD CAUSE DAMAGE TO THE HUB THAT CANNOT BE REPAIRED AND WOULD REQUIRE THAT THE HUB BE REPLACED. (1) Tools for Bulkhead Mounting CAUTION 1: DO NOT USE AN OPEN END WRENCH TO TORQUE THE HUB CLAMPING NUTS ON A SMOOTH FORGED HUB. CAUTION 2: WHEN USING THE TORQUE WRENCH ADAPTER TE457, MAKE SURE THAT IT IS CORRECTLY ENGAGED ON THE NUT BEFORE APPLYING TORQUE. (a) For three-bladed propellers that use a smooth forged hub: 1 The three-bladed smooth forged hub has less area around the heads of the hub clamping bolts than the previous design of the compact hub. 2 Torque wrench adapter Hartzell Propeller Inc. Part Number TE457 is required when torquing the hub clamping bolts for a threebladed smooth forged hub. INSTALLATION AND REMOVAL Page Rev. 21 Mar/15

94 (b) For a propeller other than a three-bladed propeller that uses a smooth forged hub: 1 Use torque wrench adapter Hartzell Propeller Inc. Part Number TE457 or other applicable torque adapter when torquing the hub clamping bolts. NOTE: Using a wrench other than Hartzell Propeller Inc. Part Number TE457 increases the risk of the wrench causing damage to the hub in the areas around the hub clamping bolts. (2) Tools for Propeller Removal or Installation: D and F Flange Propellers Safety wire pliers (Alternate: Safety cable tool) Torque wrench (1/2 inch drive) Torque wrench adapters: - Hartzell Propeller Inc. Part Number BST-2860 TE150 3/4 inch open end wrench L Flange Propellers Safety wire pliers (Alternate: Safety cable tool) Torque wrench (1/2 inch drive) Torque wrench adapters: - Hartzell Part Number BST-2860 TE150 or 5/8 inch crowfoot wrench NOTE: Using a wrench other than Hartzell Propeller Inc. Part Number BST-2860 TE150 increases the risk of the wrench causing damage to the hub in the areas around the mounting fasteners. 5/8 inch open end wrench N Flange Propellers Safety wire pliers (Alternate: Safety cable tool) Torque wrench (1/2 inch drive) Torque wrench adapter: - 7/8 inch crowfoot wrench 7/8 inch open end wrench INSTALLATION AND REMOVAL Page Rev. 21 Mar/15

95 K and R Flange Propellers Propeller Owner's Manual Safety wire pliers (Alternate: Safety cable tool) Torque wrench (1/2 inch drive) Torque wrench adapters: - Hartzell Propeller Inc. Part Number BST-2860 (TE150) or 3/4 inch crowfoot wrench NOTE: Using a wrench other than Hartzell Propeller Inc. Part Number BST-2860 TE150 increases the risk of the wrench causing damage to the hub in the areas around the mounting fasteners 3/4 inch open end wrench B. Consumables Quick Dry Stoddard Solvent or Methyl-Ethyl-Ketone (MEK) C. Expendables inch stainless steel aircraft safety wire (Alternate: inch [0.81 mm] aircraft safety cable, and associated hardware) O-ring - propeller to engine seal (see Table 3-4) INSTALLATION AND REMOVAL Page 3-5 Rev. 21 Mar/15

96 APS0212A Standard Torque Wrench Torquing Adapter 1.00 foot (304.8 mm) 0.25 foot (76.2 mm) (actual torque required) X (torque wrench length) Torque wrench reading (torque wrench length) + (length of adapter) = to achieve required actual torque EXAMPLE: reading on torque 100 Ft-Lb (136 N m) x 1.00 ft (304.8 mm) 80 Ft-Lb = wrench with 3-inch 1.00 ft (304.8 mm) ft (76.2 mm) (108 N m) < (76.2 mm) adapter for actual torque of 100 Ft-Lb (136 N m) The correction shown is for an adapter that is aligned with the centerline of the torque wrench. If the adapter is angled 90 degrees relative to the torque wrench centerline, the torque wrench reading and actual torque applied will be equal. Determining Torque Value When Using Torquing Adapter Figure 3-1 INSTALLATION AND REMOVAL Page 3-6 Rev. 14 Jan/09

97 CAUTION 1: CAUTION 2: CAUTION 3: Installation Torques MOUNTING HARDWARE MUST BE CLEAN AND DRY TO PREVENT EXCESSIVE PRELOAD OF THE MOUNTING FLANGE. ALL TORQUES LISTED ARE DRY TORQUE. REFER TO FIGURE 3-1 FOR TORQUE READING WHEN USING A TORQUE WRENCH ADAPTER. Hub clamping bolts/spinner mtg. nuts D flange propeller mtg. nuts F flange propeller mtg. nuts, except ( )HC-C3YF-5 F flange propeller mtg. nuts for ( )HC-C3YF-5 N flange propeller mtg. nuts L flange propeller mtg. nuts K and R flange propeller mtg. studs Damper assembly mtg. nuts Low pitch stop jam nut -1 Application (See Figure 6-7) Low pitch stop jam nut for -2 and -5 applications that use a one-piece spinner dome (See Figure 6-9) Low pitch stop jam nut/spinner locknut A and B for -2 and -5 applications that use a two-piece spinner dome (See Figure 6-8, Figure 3-14, and Figure 3-15) Low pitch stop jam nut -4 Application (See Figure 6-7) Governor Max. RPM Stop locking nut Torque Table Table ft-lbs (28-29 N m) ft-lbs ( N m) ft-lbs ( N m) ft-lbs ( N m) ft-lbs ( N m) ft-lbs (62-74 N m) ft-lbs (82-95 N m) ft-lbs (38-40 N m) ft-lbs (19-21 N m) ft-lbs (34-40 N m) ft-lbs (34-40 N m) ft-lbs (37-44 N m) in-lbs ( N m) INSTALLATION AND REMOVAL Page 3-7 Rev. 21 Mar/15

98 TI-0050 TI F Flange Step 1 - Torque all mounting nuts to 40 Ft-Lbs (54 N m) in the sequence shown Step 2 - Torque all mounting nuts in accordance with Table 3-1 and Figure 3-1 in the sequence shown R Flange Step 1 - Torque all mounting studs to 40 Ft-Lbs (54 N m) in the sequence shown Step 2 - Torque all mounting studs in accordance with Table 3-1 and Figure 3-1 in the sequence shown Diagram of Torquing Sequence for Propeller Mounting Hardware Figure 3-2 INSTALLATION AND REMOVAL Page 3-8 Rev. 14 Jan/09

99 2. Pre-Installation A. Inspection of Shipping Package Propeller Owner's Manual (1) Examine the exterior of the shipping container for signs of shipping damage, especially at the box ends around each blade. A hole, tear or crushed appearance at the end of the box (at the propeller tips) may indicate the propeller was dropped during shipment, possibly damaging the blades. B. Uncrating (1) Place the propeller on a firm support. (2) Remove the banding and any external wood bracing from the cardboard shipping container. (3) Remove the cardboard from the hub and blades. CAUTION: DO NOT STAND THE PROPELLER ON A BLADE TIP. (4) Put the propeller on a padded support that supports the entire length of the propeller. (5) Remove the plastic dust cover cup from the propeller mounting flange, if installed. C. Inspection after Shipment (1) After removing the propeller from the shipping container, examine the propeller components for shipping damage. D. Reassembly of a Propeller Disassembled for Shipment (1) If a propeller was received disassembled for shipment, it is to be reassembled by trained personnel in accordance with the applicable propeller maintenance manual. E. Air Charge Pressure Check (-2 and -5 Propellers) (1) Perform an air charge pressure check before propeller installation. Refer to the Air Charge section of the Maintenance Practices chapter of this manual. (a) If the air pressure loss is less than 10 percent of the specified pressure, reservice the propeller. (b) If the air pressure loss is greater than 10 percent of the specified pressure, repair the propeller. This repair must be performed at an appropriately licensed repair facility. INSTALLATION AND REMOVAL Page 3-9 Rev. 21 Mar/15

100 APS6158 HUB CLAMPING BOLTS BLADE SHANK BLADE SHANK HUB CLAMPING BOLTS Hub Clamping Bolt Location Figure 3-3 INSTALLATION AND REMOVAL Page 3-10 Rev. 14 Jan/09

101 3. Spinner Pre-Installation A. General Propeller Owner's Manual (1) The spinner support must be mounted before the propeller can be installed. The spinner will mount either to a bulkhead installed on the propeller hub, or, on some Lycoming engine installations, to an adapter attached to the starter ring gear. Follow the applicable directions in this section. (2) Refer to Figure 3-3. Remove the nuts from the hub clamping bolts that are located on either side of the blade shank. The remaining nuts/bolts should not be disturbed. Do not remove the bolts. (3) Refer to Figure 3-3. The spinner may be supplied with long hub clamping bolts. If the bolts were supplied with the spinner, remove the bolts on either side of the blade shank and replace them with the bolts supplied with the spinner. The supplied hub clamping bolts will be longer than those removed from the hub. NOTE: Depending upon the installation, the propeller hub may have been shipped from the factory with the longer hub clamping bolts installed. In this case, the hub clamping bolts will not be supplied with the spinner. INSTALLATION AND REMOVAL Page 3-11 Rev. 21 Mar/15

102 SPINNER DOME TO BULKHEAD SCREWS AND FIBER WASHER SPINNER BULKHEAD *WASHER, AREA 2 *WASHER F, AREA 1 NUT G *INSTALL A MAXIMUM OF THREE WASHERS BENEATH THE NUT IN THESE TWO LOCATIONS, I.E., ONE WASHER IN AREA 1 AND TWO WASHERS IN AREA 2 EQUAL THE MAXIMUM OF THREE WASHERS. SPINNER BULKHEAD SPACER SPINNER LOCK NUT SAFETY WIRE MAY BE INSTALLED HERE SPINNER DOME CAP SCREWS Metal Spinner Bulkhead and Spinner Mounting (Hub Mounted Spinner) Figure 3-4 APS6146 INSTALLATION AND REMOVAL Page 3-12 Rev. 14 Jan/09

103 B. Installation of a Metal Spinner Bulkhead on the Propeller Hub CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS SECTION MAY INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS. REFER TO THE ILLUSTRATED PARTS LIST CHAPTER OF THE APPLICABLE OVERHAUL MANUAL(S) FOR THE IDENTIFICATION OF SPECIFIC PROPELLER CRITICAL PARTS. (1) Refer to Figure 3-4. Put the spinner bulkhead spacers on the hub clamping bolts. Install the spinner bulkhead over the installed spacers on the hub clamping bolts. CAUTION: A MINIMUM OF ONE THREAD OF THE HUB CLAMPING BOLT MUST BE VISIBLE AFTER THE SPINNER MOUNTING NUT IS INSTALLED. (2) When the spinner bulkhead is installed, there must be no less than one thread of the hub clamping bolt exposed beyond the spinner mounting nut. A total of three washers in two areas may be installed beneath the spinner mounting nut to achieve this result. On some installations, it may be necessary to install spacers and one or more washers beneath the head of the bolt in order to avoid interference with aircraft cowling. (a) Additional washers (as many as four) may have been used during assembly of the propeller for hub clamping purposes. Description Part Number Flat Washer F B Spinner Mounting Nut G B-3599 Metal Spinner Bulkhead Mounting Hardware Table 3-2 INSTALLATION AND REMOVAL Page 3-13 Rev. 21 Mar/15

104 E6749.eps SPINNER DOME TO BULKHEAD SCREWS AND WASHER WASHER D WAVE WASHER B WASHER C SPINNER BULKHEAD NUT E SPACER A SPINNER BULKHEAD SPACER SPINNER MOUNTING NUT E Composite Bulkhead and Spinner Mounting (Hub Mounted Spinner) Figure 3-5 INSTALLATION AND REMOVAL Page 3-14 Rev. 14 Jan/09

105 1 Use the quantity of washers required when installing the bulkhead for correct spinner position, refer to Figure After the correct installation of the spinner, any remaining washers may be discarded. (3) Install at least one flat washer F and a new self-locking spinner mounting nut G on each of the hub clamping bolts used to mount the spinner bulkhead. Refer To Table 3-2. (4) Torque the nuts in accordance with Table 3-1 and Figure 3-1. C. Installation of a Composite Spinner Bulkhead on a Propeller Hub - Refer to Table 3-3 and Figure 3-5 CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS SECTION MAY INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS. REFER TO THE ILLUSTRATED PARTS LIST CHAPTER OF THE APPLICABLE OVERHAUL MANUAL(S) FOR THE IDENTIFICATION OF SPECIFIC PROPELLER CRITICAL PARTS. (1) Put a spinner bulkhead spacer A, wave washer B, and washer C on each of the hub clamping bolts. Description Part Number Spinner Bulkhead Spacer A B Wave Washer B B-7425 Washer C B Flat Washer D B-7423 Spinner Mounting Nut E B-3599 Composite Spinner Bulkhead Mounting Hardware Table 3-3 INSTALLATION AND REMOVAL Page 3-15 Rev. 22 Jul/16

106 SPINNER TO ADAPTER SCREWS AND FIBER WASHER SPINNER ADAPTER AIRCRAFT MANUFACTURER SUPPLIED HARDWARE STARTER RING GEAR SAFETY STUD PAIRS HERE Spinner Adapter and Spinner Mounting (Starter Ring Gear Mount) Figure 3-6 APS6145A INSTALLATION AND REMOVAL Page 3-16 Rev. 14 Jan/09

107 (2) Install the spinner bulkhead over the installed spacers A, wave washers B, and washers C on the hub clamping bolts. (3) Install a flat washer D and a new self-locking spinner mounting nut E on each of the hub clamping bolts used to mount the spinner bulkhead. CAUTION: A MINIMUM OF ONE THREAD OF THE HUB CLAMPING BOLT MUST BE VISIBLE AFTER THE SPINNER MOUNTING NUT IS INSTALLED. (a) When the spinner bulkhead is installed, there must be no less than one thread of the hub clamping bolt exposed beyond the spinner mounting nut E. (4) Torque each spinner mounting nut E in accordance with Table 3-1 and Figure 3-1. D. Spinner Adapter to Starter Ring Gear Installation CAUTION: INSTALL SPINNER ADAPTER BOLTS SO THAT THE BOLT HEADS ARE AT THE REAR OF THE STARTER RING GEAR AS INDICATED IN FIGURE 3-6. BOLTS INSTALLED INCORRECTLY MAY DAMAGE ENGINE COMPONENTS. (1) See Figure 3-6. Install the spinner adapter ring to the starter ring gear using the hardware supplied by the airframe manufacturer. Torque the bolts as specified by the airframe manufacturer. INSTALLATION AND REMOVAL Page 3-17 Rev. 17 Jul/12

108 Flange O-ring Stud/Bolt Nut Washer/Spacer Spring Pin D C n/a A-2044 A-7752 n/a F C n/a A-2044 A-1381* n/a K and R L except E2YL E2YL N (turbine) N (recip) C A-2067 A-2069 A-1381 B C A A-2498 A-2482 B C A (qty 2) B (qty 4) A-2498 (qty 2) A-2482 (qty 2) B (qty 4) B C n/a A-3257 A n/a C n/a A-3257 A n/a * Note: Do not install the A-1381 washer on installations that use Goodrich Corp. part number 4E1881 or 4E2058 split mounting plate. Propeller/Engine Flange O-rings and Mounting Hardware Table 3-4 INSTALLATION AND REMOVAL Page 3-18 Rev. 15 Jul/09

109 WARNING: FAILURE TO FOLLOW THESE INSTALLATION INSTRUCTIONS MAY LEAD TO PROPELLER DAMAGE, ENGINE DAMAGE, OR PROPELLER FAILURE, WHICH MAY RESULT IN DEATH, SERIOUS BODILY INJURY, AND/OR SUBSTANTIAL PROPERTY DAMAGE. UNUSUAL OR ABNORMAL VIBRATION DEMANDS IMMEDIATE INSPECTION FOR IMPROPER PROPELLER INSTALLATION. PROPELLER SEPARATION MAY OR MAY NOT BE PROCEEDED BY VIBRATION. 4. Propeller Installation CAUTION: SOME STEEL HUB PROPELLERS INCORPORATE A PHENOLIC SPACER BETWEEN THE PROPELLER AND ENGINE- MOUNTING FLANGE. WHEN INSTALLING AN ALUMINUM HUB PROPELLER, THIS SPACER IS TO BE DISCARDED. THE ALUMINUM HUB PROPELLER MOUNTING O-RING IS LOCATED ON THE INSIDE DIAMETER OF THE PROPELLER HUB. THERE SHOULD NOT BE AN O-RING ON THE ENGINE FLANGE WHEN INSTALLING AN ALUMINUM HUB PROPELLER. A. Flange Description (1) Compact propellers are manufactured with six basic hub mounting flange designs. The flange type designators are D, F, K, L, N, or R. (2) The flange type used on a particular propeller installation is indicated in the propeller model stamped on the hub. For example, HC-C2YF-4A indicates an F flange. (3) Refer to Aluminum Hub Propeller Model Identification in the Description and Operation Chapter of this manual for description of each flange type. Sample flanges are also shown in Figures 3-8 and 3-9. INSTALLATION AND REMOVAL Page 3-19 Rev. 14 Jan/09

110 D-FLNG2b ASPS6171A O-RING DOWEL STUD (SPECIAL STUD THAT ALSO FUNCTIONS AS A DOWEL PIN) STUD PROPELLER FLANGE ENGINE FLANGE NUT SPACER TORQUE WRENCH EXTENSION* TORQUE WRENCH *NOTE: If torque wrench extension is used, use the calculation in Figure 3-1 to determine correct torque wrench setting STUD DOWEL STUD (SPECIAL STUD THAT ALSO FUNCTIONS AS A DOWEL PIN) D Flange D Flange Propeller Mounting Figure 3-7 INSTALLATION AND REMOVAL Page 3-20 Rev. 14 Jan/09

111 B. Installation of D Flange Propellers Propeller Owner's Manual CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS SECTION MAY INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS. REFER TO THE ILLUSTRATED PARTS LIST CHAPTER OF THE APPLICABLE OVERHAUL MANUAL(S) FOR THE IDENTIFICATION OF SPECIFIC PROPELLER CRITICAL PARTS. (1) General (a) A D flange propeller has six 1/2 inch studs configured in a four inch circle. (b) Two special studs that also function as dowel pins, i.e., dowel studs, are also provided to transfer torque and index the propeller with respect to the engine crankshaft. Refer to Figure 3-7. (c) The dowel pin locations used on a particular propeller installation are indicated in the propeller model stamped on the hub. Refer to Aluminum Hub Propeller Model Identification in the Description and Operation Chapter of this manual. (2) Perform the applicable steps under Spinner Pre- Installation within this chapter. WARNING: CLEANING AGENTS ARE FLAMMABLE AND TOXIC TO THE SKIN, EYES, AND RESPIRATORY TRACT. SKIN AND EYE PROTECTION IS REQUIRED. AVOID PROLONGED CONTACT. USE IN WELL VENTILATED AREA. (3) Clean the engine flange and propeller flange with Quick Dry Stoddard Solvent or MEK. (4) Refer to Figure 3-7. Install the O-ring in the O-ring groove in the hub bore. Refer to Table 3-4 for the applicable O-ring and mounting hardware. NOTE: When the propeller is received from the factory, the O-ring has been installed. INSTALLATION AND REMOVAL Page 3-21 Rev. 17 Jul/12

112 WARNING: CAUTION 1: MAKE SURE THAT ANY EQUIPMENT USED TO INSTALL THE PROPELLER IS RATED UP TO 800 LBS. (363 KG) TO SUPPORT THE WEIGHT OF THE PROPELLER ASSEMBLY DURING INSTALLATION. ONE PERSON MUST NEVER ATTEMPT TO INSTALL AN UNSUPPORTED PROPELLER BY HIMSELF, REGARDLESS OF THE SIZE OR WEIGHT OF THE PROPELLER. MANUALLY LIFTING THE PROPELLER ONTO THE ENGINE CAN RESULT IN PERSONAL INJURY. A PROPELLER MUST BE CORRECTLY SUPPORTED DURING INSTALLATION ON THE ENGINE. AVOID ANY ROCKING OR SHIFTING OF THE PROPELLER WHEN IT IS PARTIALLY ENGAGED WITH THE ENGINE. ROCKING OF THE PROPELLER DURING PROPELLER INSTALLATION CAN DAMAGE THE PROPELLER HUB MOUNTING FACE, CAUSING ACTUATION OIL LEAKAGE OR DAMAGE THAT MAY SCRAP THE HUB. HUB DAMAGE CAN ALSO INTRODUCE METAL INTO THE PROPELLER OIL ACTUATION SYSTEM, WHICH COULD POSSIBLY DAMAGE THE ENGINE. CAUTION 2: WHEN INSTALLING THE PROPELLER ON THE AIRCRAFT, DO NOT DAMAGE THE ICE PROTECTION SYSTEM COMPONENTS, IF APPLICABLE. (5) With a suitable support, such as a crane hoist or similar equipment, carefully move the propeller assembly to the aircraft engine mounting flange in preparation for installation. INSTALLATION AND REMOVAL Page 3-22 Rev. 14 Jan/09

113 (6) Install the propeller on the engine flange. Make certain to align the dowel studs in the propeller flange with the corresponding holes in the engine mounting flange. (a) The propeller may be installed on the engine flange in a given position, or 180 degrees from that position. Check the engine and airframe manuals to determine if either manual specifies a propeller mounting position. CAUTION 1: MOUNTING HARDWARE MUST BE CLEAN AND DRY TO PREVENT EXCESSIVE PRELOAD OF THE MOUNTING FLANGE. CAUTION 2: TIGHTEN NUTS EVENLY TO AVOID HUB DAMAGE. (7) Install the 1/2 inch propeller mounting nuts (dry) with spacers. Refer to Table 3-4. (a) If the propeller is removed between overhaul intervals, mounting nuts may be reused if they are not damaged or corroded. (8) Torque the 1/2 inch propeller mounting nuts (dry) in accordance with Table 3-1 and Figure 3-1. (9) If required by the aircraft maintenance manual, safety all mounting studs with inch (0.81 mm) minimum diameter stainless steel wire or equivalent aircraft safety cable and associated hardware (two studs for each safety). Refer to Figure 3-4. INSTALLATION AND REMOVAL Page 3-23 Rev. 21 Mar/15

114 (10) If the propeller is equipped with an ice protection system that uses components supplied by Hartzell Propeller Inc., applicable instructions and technical information for the components supplied by Hartzell Propeller Inc. can be found in the following publications available on the Hartzell Propeller Inc. website at (a) Hartzell Propeller Inc. Manual 180 ( ) - Propeller Ice Protection System Manual (b) Hartzell Propeller Inc. Manual 181 ( ) - Propeller Ice Protection System Component Maintenance Manual (c) Hartzell Propeller Inc. Manual 182 ( ) - Propeller Electrical De-ice Boot Removal and Installation Manual (d) Hartzell Propeller Inc. Manual 183 ( ) - Propeller Anti-icing Boot Removal and Installation Manual (11) Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by the applicable TC or STC holder s Instructions for Continued Airworthiness (ICA). (12) Install the propeller spinner dome in accordance with the section Spinner Installation in this chapter. INSTALLATION AND REMOVAL Page 3-24 Rev. 21 Mar/15

115 (This page is intentionally blank.) INSTALLATION AND REMOVAL Page 3-25 Rev. 14 Jan/09

116 APS6159C DOWEL PIN O-RING PROPELLER FLANGE ENGINE FLANGE WASHER NUT TORQUE WRENCH EXTENSION* TORQUE WRENCH *NOTE: If torque wrench extension is used, use the calculation in Figure 3-1 to determine correct torque wrench setting APS6171 APS6169 F Flange N Flange F and N Flange Propeller Mounting Figure 3-8 INSTALLATION AND REMOVAL Page 3-26 Rev. 14 Jan/09

117 C. Installation of F Flange Propellers Propeller Owner's Manual CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS SECTION MAY INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS. REFER TO THE ILLUSTRATED PARTS LIST CHAPTER OF THE APPLICABLE OVERHAUL MANUAL(S) FOR THE IDENTIFICATION OF SPECIFIC PROPELLER CRITICAL PARTS. (1) General (a) An F flange propeller has six 1/2 inch studs configured in a four inch circle. (b) Two dowel pins are also provided to transfer torque and index the propeller with respect to the engine crankshaft. Refer to Figure 3-8. (c) The dowel pin locations used on a particular propeller installation are indicated in the propeller model stamped on the hub. Refer to Aluminum Hub Propeller Model Identification in the Description and Operation Chapter of this manual. (2) Perform the applicable steps under Spinner Pre- Installation within this chapter. WARNING: CLEANING AGENTS ARE FLAMMABLE AND TOXIC TO THE SKIN, EYES, AND RESPIRATORY TRACT. SKIN AND EYE PROTECTION IS REQUIRED. AVOID PROLONGED CONTACT. USE IN WELL VENTILATED AREA. (3) Clean the engine flange and propeller flange with Quick Dry Stoddard Solvent or MEK. (4) Refer to Figure 3-8. Install the O-ring in the O-ring groove in the hub bore. Refer to Table 3-4 for the applicable O-ring and mounting hardware. NOTE: When the propeller is received from the factory, the O-ring has been installed. INSTALLATION AND REMOVAL Page 3-27 Rev. 17 Jul/12

118 WARNING: CAUTION 1: MAKE SURE THAT ANY EQUIPMENT USED TO INSTALL THE PROPELLER IS RATED UP TO 800 LBS. (363 KG) TO SUPPORT THE WEIGHT OF THE PROPELLER ASSEMBLY DURING INSTALLATION. ONE PERSON MUST NEVER ATTEMPT TO INSTALL AN UNSUPPORTED PROPELLER BY HIMSELF, REGARDLESS OF THE SIZE OR WEIGHT OF THE PROPELLER. MANUALLY LIFTING THE PROPELLER ONTO THE ENGINE CAN RESULT IN PERSONAL INJURY. A PROPELLER MUST BE CORRECTLY SUPPORTED DURING INSTALLATION ON THE ENGINE. AVOID ANY ROCKING OR SHIFTING OF THE PROPELLER WHEN IT IS PARTIALLY ENGAGED WITH THE ENGINE. ROCKING OF THE PROPELLER DURING PROPELLER INSTALLATION CAN DAMAGE THE PROPELLER HUB MOUNTING FACE, CAUSING ACTUATION OIL LEAKAGE OR DAMAGE THAT MAY SCRAP THE HUB. HUB DAMAGE CAN ALSO INTRODUCE METAL INTO THE PROPELLER OIL ACTUATION SYSTEM, WHICH COULD POSSIBLY DAMAGE THE ENGINE. CAUTION 2: WHEN INSTALLING THE PROPELLER ON THE AIRCRAFT, DO NOT DAMAGE THE ICE PROTECTION SYSTEM COMPONENTS, IF APPLICABLE. (5) With a suitable support, such as a crane hoist or similar equipment, carefully move the propeller assembly to the aircraft engine mounting flange in preparation for installation. INSTALLATION AND REMOVAL Page 3-28 Rev. 21 Mar/15

119 (6) Install the propeller on the engine flange. Make certain to align the dowel pins in the propeller flange with the corresponding holes in the engine mounting flange. (a) The propeller may be installed on the engine flange in a given position, or 180 degrees from that position. Check the engine and airframe manuals to determine if either manual specifies a propeller mounting position. CAUTION 1: MOUNTING HARDWARE MUST BE CLEAN AND DRY TO PREVENT EXCESSIVE PRELOAD OF THE MOUNTING FLANGE. CAUTION 2: TIGHTEN NUTS EVENLY TO AVOID HUB DAMAGE. (7) Install the 1/2 inch propeller mounting nuts (dry) with washers. Refer to Table 3-4. (a) If the propeller is removed between overhaul intervals, mounting nuts may be reused if they are not damaged or corroded. (8) Torque the 1/2 inch propeller mounting nuts (dry) in accordance with Table 3-1, Figure 3-1 and Figure 3-2. (9) If required by the aircraft maintenance manual, safety all mounting studs with inch (0.81 mm) minimum diameter stainless steel wire or equivalent aircraft safety cable and associated hardware (two studs for each safety). Refer to Figure 3-4. INSTALLATION AND REMOVAL Page 3-29 Rev. 21 Mar/15

120 (10) If the propeller is equipped with an ice protection system that uses components supplied by Hartzell Propeller Inc., applicable instructions and technical information for the components supplied by Hartzell Propeller Inc. can be found in the following publications available on the Hartzell Propeller Inc. website at (a) Hartzell Propeller Inc. Manual 180 ( ) - Propeller Ice Protection System Manual (b) Hartzell Propeller Inc. Manual 181 ( ) - Propeller Ice Protection System Component Maintenance Manual (c) Hartzell Propeller Inc. Manual 182 ( ) - Propeller Electrical De-ice Boot Removal and Installation Manual (d) Hartzell Propeller Inc. Manual 183 ( ) - Propeller Anti-icing Boot Removal and Installation Manual (11) Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by the applicable TC or STC holder s Instructions for Continued Airworthiness (ICA). (12) Install the propeller spinner dome in accordance with the section Spinner Installation in this chapter. INSTALLATION AND REMOVAL Page 3-30 Rev. 21 Mar/15

121 D. Installation of N Flange Propellers (1) General Propeller Owner's Manual (a) An N flange propeller has eight 9/16 inch studs configured in a 4.25 inch circle. (b) Two dowel pins are also provided to transfer torque and index the propeller with respect to the engine crankshaft. Refer to Figure 3-8. (c) The dowel pin locations used on a particular propeller installation are indicated in the propeller model stamped on the hub. Refer to Aluminum Hub Propeller Model Identification in the Description and Operation Chapter of this manual. (2) Perform the applicable steps under Spinner Pre- Installation within this chapter. WARNING: CLEANING AGENTS ARE FLAMMABLE AND TOXIC TO THE SKIN, EYES, AND RESPIRATORY TRACT. SKIN AND EYE PROTECTION IS REQUIRED. AVOID PROLONGED CONTACT. USE IN WELL VENTILATED AREA. (3) Clean the engine flange and propeller flange with Quick Dry Stoddard Solvent or MEK. (4) Refer to Figure 3-8. Install the O-ring on the engine flange. Refer to Table 3-4 for the applicable O-ring and mounting hardware. NOTE: When the propeller is received from the factory, the O-ring has been installed. INSTALLATION AND REMOVAL Page 3-31 Rev. 21 Mar/15

122 WARNING: MAKE SURE THAT ANY EQUIPMENT USED TO INSTALL THE PROPELLER IS RATED UP TO 800 LBS. (363 KG) TO SUPPORT THE WEIGHT OF THE PROPELLER ASSEMBLY DURING INSTALLATION. ONE PERSON MUST NEVER ATTEMPT TO INSTALL AN UNSUPPORTED PROPELLER BY HIMSELF, REGARDLESS OF THE SIZE OR WEIGHT OF THE PROPELLER. MANUALLY LIFTING THE PROPELLER ONTO THE ENGINE CAN RESULT IN PERSONAL INJURY. CAUTION 1: A PROPELLER MUST BE CORRECTLY SUPPORTED DURING INSTALLATION ON THE ENGINE. AVOID ANY ROCKING OR SHIFTING OF THE PROPELLER WHEN IT IS PARTIALLY ENGAGED WITH THE ENGINE. ROCKING OF THE PROPELLER DURING PROPELLER INSTALLATION CAN DAMAGE THE PROPELLER HUB MOUNTING FACE, CAUSING ACTUATION OIL LEAKAGE OR DAMAGE THAT MAY SCRAP THE HUB. HUB DAMAGE CAN ALSO INTRODUCE METAL INTO THE PROPELLER OIL ACTUATION SYSTEM, WHICH COULD POSSIBLY DAMAGE THE ENGINE. CAUTION 2: WHEN INSTALLING THE PROPELLER ON THE AIRCRAFT, DO NOT DAMAGE THE ICE PROTECTION SYSTEM COMPONENTS, IF APPLICABLE. (5) With a suitable support, such as a crane hoist or similar equipment, carefully move the propeller assembly to the aircraft engine mounting flange in preparation for installation. INSTALLATION AND REMOVAL Page 3-32 Rev. 21 Mar/15

123 (6) Install the propeller on the engine flange. Make certain to align the dowel pins in the propeller flange with the corresponding holes in the engine mounting flange. (a) The propeller may be installed on the engine flange in a given position, or 180 degrees from that position. Check the engine and airframe manuals to determine if either manual specifies a propeller mounting position. CAUTION 1: MOUNTING HARDWARE MUST BE CLEAN AND DRY TO PREVENT EXCESSIVE PRELOAD OF THE MOUNTING FLANGE. CAUTION 2: TIGHTEN NUTS EVENLY TO AVOID HUB DAMAGE. (7) Install the 9/16 inch propeller mounting nuts (dry) with washers. Refer to Table 3-4. (a) If the propeller is removed between overhaul intervals, mounting nuts may be reused if they are not damaged or corroded. (8) Torque the 9/16 inch propeller mounting nuts (dry) in accordance with Table 3-1 and Figure 3-1. (9) If required by the aircraft maintenance manual, safety all mounting studs with inch (0.81 mm) minimum diameter stainless steel wire or equivalent aircraft safety cable and associated hardware (two studs for each safety). Refer to Figure 3-4. INSTALLATION AND REMOVAL Page 3-33 Rev. 21 Mar/15

124 (10) If the propeller is equipped with an ice protection system that uses components supplied by Hartzell Propeller Inc., applicable instructions and technical information for the components supplied by Hartzell Propeller Inc. can be found in the following publications available on the Hartzell Propeller Inc. website at (a) Hartzell Propeller Inc. Manual 180 ( ) - Propeller Ice Protection System Manual (b) Hartzell Propeller Inc. Manual 181 ( ) - Propeller Ice Protection System Component Maintenance Manual (c) Hartzell Propeller Inc. Manual 182 ( ) - Propeller Electrical De-ice Boot Removal and Installation Manual (d) Hartzell Propeller Inc. Manual 183 ( ) - Propeller Anti-icing Boot Removal and Installation Manual (11) Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by the applicable TC or STC holder s Instructions for Continued Airworthiness (ICA). (12) Install the propeller spinner dome in accordance with the section Spinner Installation in this chapter. INSTALLATION AND REMOVAL Page 3-34 Rev. 21 Mar/15

125 (This page is intentionally blank.) INSTALLATION AND REMOVAL Page 3-35 Rev. 21 Mar/15

126 TORQUE WRENCH EXTENSION* HARTZELL PART NUMBER BST-2860 TORQUE WRENCH SPRING PIN NUT WASHER PROPELLER FLANGE STARTER RING GEAR O-RING (INSTALLED IN HUB) ENGINE FLANGE *NOTE: When using the torque wrench extension, use the calculation in Figure 3-1 to determine correct torque wrench setting APS6170 APS6168 APS6172 L Flange K Flange R Flange APS6160D L, K, and R Flange Propeller Mounting - Figure 3-9 INSTALLATION AND REMOVAL Page 3-36 Rev. 21 Mar/15

127 E. Installation of L Flange Propellers, Except Model HC-E2YL-( ) CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS SECTION MAY INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS. REFER TO THE ILLUSTRATED PARTS LIST CHAPTER OF THE APPLICABLE OVERHAUL MANUAL(S) FOR THE IDENTIFICATION OF SPECIFIC PROPELLER CRITICAL PARTS. (1) General (a) An L flange is an SAE No. 2 flange with six 7/16 inch studs configured in a 4.75 inch circle. (b) Four drive bushings transfer torque and index the propeller with respect to the engine crankshaft. The bushings are located on the engine flange and fit into openings on the propeller flange. Refer to Figure 3-9. (c) The bushing locations used on a particular propeller installation are indicated in the propeller model stamped on the hub. Refer to Aluminum Hub Propeller Model Identification in the Description and Operation chapter of this manual. (2) Perform the appropriate steps in the Spinner Pre- Installation section in this chapter. WARNING: CLEANING AGENTS ARE FLAMMABLE AND TOXIC TO THE SKIN, EYES, AND RESPIRATORY TRACT. SKIN AND EYE PROTECTION ARE REQUIRED. AVOID PROLONGED CONTACT. USE IN WELL VENTILATED AREA. (3) Clean the engine flange and propeller flange with Quick Dry Stoddard Solvent or MEK. INSTALLATION AND REMOVAL Page 3-37 Rev. 21 Mar/15

128 (4) Refer to Figure 3-9. Install the O-ring in the O-ring groove in the rear of the hub. Refer to Table 3-4 for the applicable O-ring and mounting hardware. NOTE: When the propeller is received from the factory, the O-ring has been installed. WARNING: CAUTION 1: MAKE SURE THAT ANY EQUIPMENT USED TO INSTALL THE PROPELLER IS RATED UP TO 800 LBS. (363 KG) TO SUPPORT THE WEIGHT OF THE PROPELLER ASSEMBLY DURING INSTALLATION. ONE PERSON MUST NEVER ATTEMPT TO INSTALL AN UNSUPPORTED PROPELLER BY HIMSELF, REGARDLESS OF THE SIZE OR WEIGHT OF THE PROPELLER. MANUALLY LIFTING THE PROPELLER ONTO THE ENGINE CAN RESULT IN PERSONAL INJURY. A PROPELLER MUST BE CORRECTLY SUPPORTED DURING INSTALLATION ON THE ENGINE. AVOID ANY ROCKING OR SHIFTING OF THE PROPELLER WHEN IT IS PARTIALLY ENGAGED WITH THE ENGINE. ROCKING OF THE PROPELLER DURING PROPELLER INSTALLATION CAN DAMAGE THE PROPELLER HUB MOUNTING FACE, CAUSING ACTUATION OIL LEAKAGE OR DAMAGE THAT MAY SCRAP THE HUB. HUB DAMAGE CAN ALSO INTRODUCE METAL INTO THE PROPELLER OIL ACTUATION SYSTEM, WHICH COULD POSSIBLY DAMAGE THE ENGINE. INSTALLATION AND REMOVAL Page 3-38 Rev. 21 Mar/15

129 CAUTION 2: WHEN INSTALLING THE PROPELLER ON THE AIRCRAFT, DO NOT DAMAGE THE ICE PROTECTION SYSTEM COMPONENTS, IF APPLICABLE. (5) With a suitable support, such as a crane hoist or similar equipment, carefully move the propeller assembly to the aircraft engine mounting flange in preparation for installation. (6) Install the propeller on the engine flange. Align the engine flange bushings with the corresponding holes in the propeller flange. (a) The propeller may be installed on the engine flange in a given position, or 180 degrees from that position. Check the engine and airframe manuals to determine if either manual specifies a propeller mounting position. CAUTION 1: MOUNTING HARDWARE MUST BE CLEAN AND DRY TO PREVENT EXCESSIVE PRELOAD OF THE MOUNTING FLANGE. CAUTION 2: TIGHTEN NUTS EVENLY TO AVOID HUB DAMAGE. (7) Torque the 7/16 inch propeller mounting studs (dry) in accordance with Table 3-1 and Figure 3-1. (8) If required by the aircraft maintenance manual, safety all mounting studs with inch (0.81 mm) minimum diameter stainless steel wire or equivalent aircraft safety cable and associated hardware (two studs for each safety). Refer to Figure 3-6. (a) If the propeller is removed between overhaul intervals, mounting studs may be reused if they are not damaged or corroded. INSTALLATION AND REMOVAL Page 3-39 Rev. 21 Mar/15

130 (9) If the propeller is equipped with an ice protection system that uses components supplied by Hartzell Propeller Inc., applicable instructions and technical information for the components supplied by Hartzell Propeller Inc. can be found in the following publications available on the Hartzell Propeller Inc. website at (a) Hartzell Propeller Inc. Manual 180 ( ) - Propeller Ice Protection System Manual (b) Hartzell Propeller Inc. Manual 181 ( ) - Propeller Ice Protection System Component Maintenance Manual (c) Hartzell Propeller Inc. Manual 182 ( ) - Propeller Electrical De-ice Boot Removal and Installation Manual (d) Hartzell Propeller Inc. Manual 183 ( ) - Propeller Anti-icing Boot Removal and Installation Manual (10) Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by the applicable TC or STC holder s Instructions for Continued Airworthiness (ICA). (11) Install the propeller spinner dome in accordance with the section Spinner Installation in this chapter. INSTALLATION AND REMOVAL Page 3-40 Rev. 21 Mar/15

131 (This page is intentionally blank.) INSTALLATION AND REMOVAL Page 3-41 Rev. 21 Mar/15

132 F. Installation of HC-E2YL-( ) Propellers CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS SECTION MAY INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS. REFER TO THE ILLUSTRATED PARTS LIST CHAPTER OF THE APPLICABLE OVERHAUL MANUAL(S) FOR THE IDENTIFICATION OF SPECIFIC PROPELLER CRITICAL PARTS. (1) General (a) An E2YL flange has four 7/16 inch studs and two 7/16 inch bolts configured in a 4.75 inch circle. (b) Four drive bushings transfer torque and index the propeller with respect to the engine crankshaft. The bushings are located on the engine flange and fit into openings on the propeller flange. Refer to Figure 3-7. (c) The bushing location used on this propeller installation is indicated in the propeller model. Refer to Aluminum Hub Propeller Model Identification in the Description and Operation chapter of this manual. (2) Perform the applicable steps in the Spinner Preinstallation section in this chapter. WARNING: CLEANING AGENTS ARE FLAMMABLE AND TOXIC TO THE SKIN, EYES, AND RESPIRATORY TRACT. SKIN AND EYE PROTECTION ARE REQUIRED. AVOID PROLONGED CONTACT. USE IN WELL VENTILATED AREA. (3) Clean the engine flange and propeller flange with Quick Dry Stoddard Solvent or MEK. INSTALLATION AND REMOVAL Page 3-42 Rev. 21 Mar/15

133 (4) Refer to Figure 3-9. Install the O-ring in the O-ring groove in the rear of the hub. Refer to Table 3-4 for the applicable O-ring and mounting hardware. NOTE: When the propeller is received from the factory, the O-ring has been installed. WARNING: CAUTION 1: MAKE SURE THAT ANY EQUIPMENT USED TO INSTALL THE PROPELLER IS RATED UP TO 800 LBS. (363 KG) TO SUPPORT THE WEIGHT OF THE PROPELLER ASSEMBLY DURING INSTALLATION. ONE PERSON MUST NEVER ATTEMPT TO INSTALL AN UNSUPPORTED PROPELLER BY HIMSELF, REGARDLESS OF THE SIZE OR WEIGHT OF THE PROPELLER. MANUALLY LIFTING THE PROPELLER ONTO THE ENGINE CAN RESULT IN PERSONAL INJURY. A PROPELLER MUST BE CORRECTLY SUPPORTED DURING INSTALLATION ON THE ENGINE. AVOID ANY ROCKING OR SHIFTING OF THE PROPELLER WHEN IT IS PARTIALLY ENGAGED WITH THE ENGINE. ROCKING OF THE PROPELLER DURING PROPELLER INSTALLATION CAN DAMAGE THE PROPELLER HUB MOUNTING FACE, CAUSING ACTUATION OIL LEAKAGE OR DAMAGE THAT MAY SCRAP THE HUB. HUB DAMAGE CAN ALSO INTRODUCE METAL INTO THE PROPELLER OIL ACTUATION SYSTEM, WHICH COULD POSSIBLY DAMAGE THE ENGINE. INSTALLATION AND REMOVAL Page 3-43 Rev. 21 Mar/15

134 CAUTION 2: WHEN INSTALLING THE PROPELLER ON THE AIRCRAFT, DO NOT DAMAGE THE ICE PROTECTION SYSTEM COMPONENTS, IF APPLICABLE. (5) With a suitable support, such as a crane hoist or similar equipment, carefully move the propeller assembly to the aircraft engine mounting flange in preparation for installation. (6) Install the propeller on the engine flange. Align the engine flange bushings with the corresponding holes in the propeller flange. (a) The propeller may be installed on the engine flange in a given position, or 180 degrees from that position. Refer to the engine and airframe manuals to determine if either manual specifies a propeller mounting position. CAUTION 1: MOUNTING HARDWARE MUST BE CLEAN AND DRY TO PREVENT EXCESSIVE PRELOAD OF THE MOUNTING FLANGE. CAUTION 2: TIGHTEN NUTS EVENLY TO AVOID HUB DAMAGE. (7) Install the 7/16 inch propeller mounting bolts (dry) with washers. Refer to Table 3-4. (a) If the propeller is removed between overhaul intervals, mounting bolts and studs may be reused if they are not damaged or corroded. (8) Torque the 7/16 inch nuts on the propeller mounting studs (dry) and the 7/16 inch bolts (dry) in accordance with Table 3-1 and Figure 3-1. (9) If required by the aircraft maintenance manual, safety all mounting studs with inch (0.81 mm) minimum diameter stainless steel wire or equivalent aircraft safety cable and associated hardware (two studs for each safety). Refer to Figure 3-6. INSTALLATION AND REMOVAL Page 3-44 Rev. 21 Mar/15

135 (10) If the propeller is equipped with an ice protection system that uses components supplied by Hartzell Propeller Inc., applicable instructions and technical information for the components supplied by Hartzell Propeller Inc. can be found in the following publications available on the Hartzell Propeller Inc. website at (a) Hartzell Propeller Inc. Manual 180 ( ) - Propeller Ice Protection System Manual (b) Hartzell Propeller Inc. Manual 181 ( ) - Propeller Ice Protection System Component Maintenance Manual (c) Hartzell Propeller Inc. Manual 182 ( ) - Propeller Electrical De-ice Boot Removal and Installation Manual (d) Hartzell Propeller Inc. Manual 183 ( ) - Propeller Anti-icing Boot Removal and Installation Manual (11) Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by the applicable TC or STC holder s Instructions for Continued Airworthiness (ICA). (12) Install the propeller spinner dome in accordance with the section Spinner Installation in this chapter. INSTALLATION AND REMOVAL Page 3-45 Rev. 21 Mar/15

136 G. Installation of K and R Flange Propellers CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS SECTION MAY INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS. REFER TO THE ILLUSTRATED PARTS LIST CHAPTER OF THE APPLICABLE OVERHAUL MANUAL(S) FOR THE IDENTIFICATION OF SPECIFIC PROPELLER CRITICAL PARTS. (1) General (a) A K or R flange is an SAE No. 2 flange that has six 1/2 inch studs configured in a 4.75 inch circle. (b) Four ( K flange) or five ( R flange) drive bushings transfer torque and index the propeller with respect to the engine crankshaft. The bushings are located on the engine flange and fit into counter bored holes on the propeller flange. Refer to Figure 3-9. (c) An R flange propeller may be installed on a K engine flange. A K flange propeller cannot be installed on an R flange engine. (d) The bushing locations used on a particular propeller installation are indicated in the propeller model stamped on the hub. Refer to Aluminum Hub Propeller Model Identification in the Description and Operation chapter of this manual. (2) Perform the applicable steps under Spinner Pre- Installation within this chapter. WARNING: CLEANING AGENTS ARE FLAMMABLE AND TOXIC TO THE SKIN, EYES AND RESPIRATORY TRACT. SKIN AND EYE PROTECTION IS REQUIRED. AVOID PROLONGED CONTACT. USE IN WELL VENTILATED AREA. (3) Clean the engine flange and propeller flange with Quick Dry Stoddard Solvent or MEK. INSTALLATION AND REMOVAL Page 3-46 Rev. 21 Mar/15

137 (4) See Figure 3-9. Install the O-ring in the O-ring groove in the rear of the hub. See Table 3-4 for the applicable O-ring and mounting hardware. NOTE: When the propeller is received from the factory, the O-ring has been installed. WARNING: CAUTION 1: MAKE SURE THAT ANY EQUIPMENT USED TO INSTALL THE PROPELLER IS RATED UP TO 800 LBS. (363 KG) TO SUPPORT THE WEIGHT OF THE PROPELLER ASSEMBLY DURING INSTALLATION. ONE PERSON MUST NEVER ATTEMPT TO INSTALL AN UNSUPPORTED PROPELLER BY HIMSELF, REGARDLESS OF THE SIZE OR WEIGHT OF THE PROPELLER. MANUALLY LIFTING THE PROPELLER ONTO THE ENGINE CAN RESULT IN PERSONAL INJURY. A PROPELLER MUST BE CORRECTLY SUPPORTED DURING INSTALLATION ON THE ENGINE. AVOID ANY ROCKING OR SHIFTING OF THE PROPELLER WHEN IT IS PARTIALLY ENGAGED WITH THE ENGINE. ROCKING OF THE PROPELLER DURING PROPELLER INSTALLATION CAN DAMAGE THE PROPELLER HUB MOUNTING FACE, CAUSING ACTUATION OIL LEAKAGE OR DAMAGE THAT MAY SCRAP THE HUB. HUB DAMAGE CAN ALSO INTRODUCE METAL INTO THE PROPELLER OIL ACTUATION SYSTEM, WHICH COULD POSSIBLY DAMAGE THE ENGINE. INSTALLATION AND REMOVAL Page 3-47 Rev. 21 Mar/15

138 CAUTION 2: WHEN INSTALLING THE PROPELLER ON THE AIRCRAFT, DO NOT DAMAGE THE ICE PROTECTION SYSTEM COMPONENTS, IF APPLICABLE. (5) With a suitable support, such as a crane hoist or similar equipment, carefully move the propeller assembly to the aircraft engine mounting flange in preparation for installation. (6) Install the propeller on the engine flange. Align the engine flange bushings with the corresponding holes in the propeller flange. (a) An R flange propeller may be installed on a K engine flange in a given position, or 180 degrees from that position. (b) An R flange propeller may be installed on an R engine flange in one position only. (c) A K flange propeller may be installed only on a K engine flange, but may be installed in a given position, or 180 degrees from that position. (d) Check the engine and airframe manuals to determine if either manual specifies a propeller mounting position. CAUTION 1: MOUNTING HARDWARE MUST BE CLEAN AND DRY TO PREVENT EXCESSIVE PRELOAD OF THE MOUNTING FLANGE. CAUTION 2: TIGHTEN NUTS EVENLY TO AVOID HUB DAMAGE. (7) Torque the 1/2 inch propeller mounting studs (dry) in accordance with Table 3-1, Figure 3-1, and Figure 3-2. (8) If required by the aircraft maintenance manual, safety all mounting studs with inch (0.81 mm) minimum diameter stainless steel wire or equivalent aircraft safety cable and associated hardware (two studs for each safety). Refer to Figure 3-6. (a) If the propeller is removed between overhaul intervals, mounting studs may be reused if they are not damaged or corroded. INSTALLATION AND REMOVAL Page 3-48 Rev. 21 Mar/15

139 (9) If the propeller is equipped with an ice protection system that uses components supplied by Hartzell Propeller Inc., applicable instructions and technical information for the components supplied by Hartzell Propeller Inc. can be found in the following publications available on the Hartzell Propeller Inc. website at (a) Manual 180 ( ) - Propeller Ice Protection System Manual (b) Manual 181 ( ) - Propeller Ice Protection System Component Maintenance Manual (c) Manual 182 ( ) - Propeller Electrical De-ice Boot Removal and Installation Manual (d) Manual 183 ( ) - Propeller Anti-icing Boot Removal and Installation Manual (10) Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by the applicable TC or STC holder s Instructions for Continued Airworthiness (ICA). (11) Install the propeller spinner dome in accordance with the section Spinner Installation in this chapter. INSTALLATION AND REMOVAL Page 3-49 Rev. 21 Mar/15

140 TI B Washer B Nut A-1584 Hex Head Bolt C-1576 Damper Assembly A Spacer A Spacer Damper Installation Figure 3-10 Dome or Cap Washer Screw Metal Spinner Dome A-1020 Fiber B , Truss Head Metal Spinner Cap n/a B , 100 Head, Cres Composite Spinner Dome B L Dimpled, 100, Cres. B , 100 Head, Cres Spinner Dome and Spinner Cap Mounting Hardware Table 3-5 INSTALLATION AND REMOVAL Page 3-50 Rev. 21 Mar/15

141 5. Damper Installation Propeller Owner's Manual A. Installation of C-1576 Damper (Hartzell Propeller Inc. Kit A-1583) CAUTION: USE WITH A SPINNER MOUNTING KIT ONLY. (1) Use the A spinner mounting kit when installing the C-1576 damper assembly (Figure 3-10). (a) Remove four of the B washers from the A spinner mounting kit when installing the C-1576 damper assembly. (2) Install the propeller spinner dome and cap in accordance with the section Spinner Installation in this chapter. 6. Spinner Installation CAUTION: TO PREVENT DAMAGE TO THE BLADE AND BLADE PAINT, WRAP THE BLADE SHANKS IN SEVERAL LAYERS OF MASKING OR DUCT TAPE BEFORE INSTALLING THE SPINNER DOME. REMOVE THE TAPE AFTER THE SPINNER IS INSTALLED. A. Installing a One-Piece Spinner Dome, Except Spinner Assembly C-3567-(4,8) With a D (P) Spinner Dome (1) The following instructions relate to Hartzell Propeller Inc. spinners only. In some cases, the airframe manufacturer produced the spinner assembly. If so, refer to the airframe manufacturer s manual for spinner installation instructions. (2) Examine the low pitch stop hardware configuration. (a) If the visual examination shows that the hardware configuration is one hex nut safety wired to a set screw, no further action is required. (b) If the visual examination shows that the hardware configuration is not one hex nut safety wired to a set screw, modify the propeller assembly to the hardware configuration of one hex nut safety wired to a set screw in accordance with the section Modification of the Low Pitch Stop Hardware in the Maintenance Practices chapter of this manual. INSTALLATION AND REMOVAL Page 3-51 Rev. 21 Mar/15

142 (3) Examine the interior of the spinner dome. If the spinner dome has an internal support (see Figure 2-3) that encircles the propeller cylinder, the cylinder may need to be wrapped with one or more layers of UHMW tape (Hartzell Propeller Inc. P/N B ). (a) When the spinner dome has been removed to facilitate maintenance, check the spinner internal support to cylinder fit. If the spinner loosens in service, add one or more layers of UHMW tape to the cylinder until the spinner fits snugly. CAUTION: THE SPINNER DOME INTERNAL SUPPORT MUST FIT SNUGLY ON CYLINDER. AN IMPROPERLY SUPPORTED DOME COULD CAUSE CYLINDER DAMAGE OR A CRACK IN THE DOME OR BULKHEAD. (4) Install the spinner and check for a snug fit where the internal support contacts the cylinder. If the support does not fit snugly on the cylinder, apply a layer of UHMW tape and recheck. Repeat until the spinner support fits snugly on the cylinder. CAUTION: TO AVOID DAMAGING THE AIRCRAFT COWLING, THE SCREWS MUST NOT EXTEND MORE THAN THREE THREADS PAST THE BULKHEAD NUTPLATES. (5) Using the supplied screws and washers, attach the spinner dome to the spinner bulkhead. Refer to Table 3-5. (a) Install a screw in each of the one or two holes centered between two blade cutouts. (b) Tighten the screw(s) until snug. (c) Install a screw in each of the one or two holes centered between two blade cutouts on the opposite side of the spinner dome. (d) Tighten the screw(s) until snug. (e) Repeat the installation of the screws in the holes centered between two blade cutouts for the remaining areas. INSTALLATION AND REMOVAL Page 3-52 Rev. 22 Jul/16

143 (f) Tighten the screws until snug. (g) Install the remaining screws in the remaining holes. (h) Tighten the screws until snug. INSTALLATION AND REMOVAL Page 3-53 Rev. 22 Jul/16

144 Cylinder B-5486 Spinner Mounting Spacers Spacer Base Raised Surface TPI-MB-0032 Installing the Spacer Base and Spinner Mounting Spacers Figure 3-11 INSTALLATION AND REMOVAL Page 3-54 Rev. 21 Mar/15

145 B. Installing Spinner Assembly C-3567-(4,8) With a D (P) Spinner Dome (1) General (a) This section provides instructions for installing a redesigned C-3567-(4,8)(P) spinner assembly that includes a D (P) spinner dome and the following forward support components: Plastic Forward Bulkhead Spacer Base 3 B-5486 Spinner Mounting Spacer NOTE: The forward support components are not compatible with the D (P) spinner dome used on the previous design. (b) The redesigned C-3567-(4,8)(P) spinner assembly may be used with the previous design of the C-3567-(4, 8)(P) spinner assembly on the same aircraft. 1 The redesigned spinner dome has the same shape and finish as the previous design and appears identical when installed on the aircraft. (2) Procedure (a) Install the C-3566-(13,15)(P) bulkhead unit in accordance with the applicable paragraphs in the section Spinner Pre-Installation in this chapter. (b) Put the spacer base on the cylinder with the radiused side of the spacer base against the raised surface on the cylinder. Refer to Figure (c) Put ten B-5486 spinner mounting spacers on the cylinder on top of the spacer base. NOTE: The B-5486 spinner mounting spacers are used to adjust the spinner dome preload. Spacers may be added or removed after pre-fitting the spinner dome later in this procedure. INSTALLATION AND REMOVAL Page 3-55 Rev. 21 Mar/15

146 Plastic Forward Bulkhead Cylinder B-5486 Spinner Mounting Spacers D (P) Spinner Dome C-3566-(13,15)(P) Bulkhead Unit Plastic Forward Bulkhead Cylinder UHMW Tape (as required) B-5486 Spinner Mounting Spacers TPI-MB-0034 Install the Plastic Forward Bulkhead and Pre-fit the Spinner Dome Figure 3-12 INSTALLATION AND REMOVAL Page 3-56 Rev. 21 Mar/15

147 (d) Put the plastic forward bulkhead over the cylinder on top of the B-5486 spinner mounting spacers. Refer to Figure CAUTION: THE PLASTIC FORWARD BULKHEAD MUST FIT SNUGLY ON THE CYLINDER. IF THE PLASTIC FORWARD BULKHEAD IS LOOSE, IT MAY RESULT IN DAMAGE TO THE CYLINDER. (e) Pre-fit the D (P) spinner dome. Refer to Figure Put the spinner dome over the plastic forward bulkhead and gently push the spinner dome as far aft as it will go onto the C-3566-(13,15)(P) bulkhead unit. a Do not install mounting hardware at this time. 2 Holding the spinner dome on opposite sides, carefully try to shift the dome from side-to-side. 3 If the spinner dome shifts easily, the plastic forward bulkhead may not be snug on the cylinder. a Remove the spinner dome and the plastic forward bulkhead. CAUTION: IF APPLYING UHMW TAPE TO THE OUTER DIAMETER OF THE CYLINDER, DO NOT COVER ANY LABELS. b Apply UHMW tape CM137 or equivalent, to the inside diameter of the plastic forward bulkhead or to the outer diameter of the cylinder. (1) Strips of UHMW tape approximately 2 inches (50 mm) long may be applied from front to back at evenly spaced locations around the inside diameter of the plastic forward bulkhead. Refer to Figure INSTALLATION AND REMOVAL Page 3-57 Rev. 21 Mar/15

148 Fluorglas Tape or UHMW Tape (Hartzell Propeller Inc. P/N B ) Tape wrapped over the trailing edge of the forward bulkhead TPI TPI Optional Tape on the Forward Bulkhead Figure INSTALLATION AND REMOVAL Page 3-58 Rev. 22 Jul/16

149 Spinner dome mounting hole away from the bulkhead (this is the correct alignment) Bulkhead Mounting Hole Bulkhead Mounting Hole Spinner dome mounting hole toward the bulkhead (additional B-5486 spacers required) B Screw A-1020 Fiber Washer D (P) Spinner Dome Awl C-3566-(13,15)(P) Bulkhead Unit TPI-MB-0033 Spinner Dome Mounting Hole Alignment Figure 3-13 INSTALLATION AND REMOVAL Page Rev. 22 Jul/16

150 (2) UHMW tape may be applied around the entire circumference of the inside diameter of the plastic forward bulkhead. (3) UHMW tape may be applied around the outer diameter of the cylinder where the plastic forward bulkhead will be installed. c Repeat steps 6.B.(2)(d) and 6.B.(2)(e). (1) If the spinner dome shifts easily, apply additional layer(s) of UHMW tape until a snug fit is achieved. 4 Optionally, for a spinner dome that has a removable forward bulkhead, apply a layer of fluorglas tape or UHMW tape (Hartzell Propeller Inc. P/N B ) on the outboard flange of the forward bulkhead to prevent contact between the forward bulkhead and the spinner dome. WARNING: CLEANING AGENTS ARE FLAMMABLE AND TOXIC TO THE SKIN, EYES, AND RESPIRATORY TRACT. SKIN AND EYE PROTECTION IS REQUIRED. AVOID PROLONGED CONTACT. USE IN WELL VENTILATED AREA. a Using acetone, denatured alcohol, or MEK, clean the area where the tape will be applied. b Cut eight pieces of tape that are approximately three inches (76 mm) long. c Apply the pieces of tape in equally spaced locations on the forward bulkhead as shown in Figure d Tape may be wrapped over the trailing edge of the forward bulkhead as necessary. 5 If the spinner dome does not shift, continue to the next step. INSTALLATION AND REMOVAL Page Rev. 22 Jul/16

151 (f) Gently push the D (P) spinner dome as far aft as it will go onto the C-3566-(13,15)(P) bulkhead unit. Refer to Figure (g) Examine the alignment of the mounting holes in the D (P) spinner dome and the C-3566-(13,15)(P) bulkhead unit. 1 The spinner dome mounting holes must be away from the bulkhead unit in relation to the bulkhead mounting holes. 2 Approximately 50% of the diameter of each bulkhead unit mounting hole should be visible through the spinner dome mounting holes. NOTE: The temporary misalignment of the mounting holes is necessary to get the correct preload of the spinner dome. 3 If the mounting hole position is incorrect, add or remove B-5486 spinner mounting spacers as necessary to get proper alignment. a Remove the spinner dome and the plastic forward bulkhead. b Add or remove B-5486 spinner mounting spacer(s) as required. c Repeat steps 6.B.(2)(d) thru 6.B.(2)(g). 4 If the mounting hole position is correct, continue to the next step. INSTALLATION AND REMOVAL Page 3-59 Rev. 22 Jul/16

152 (h) Using the supplied screws and washers, attach the spinner dome to the spinner bulkhead. Refer to Table Install a screw in each of the one or two holes centered between two blade cutouts. 2 Tighten the screw(s) until snug. 3 Install a screw in each of the one or two holes centered between two blade cutouts on the opposite side of the spinner dome. 4 Tighten the screw(s) until snug. 5 Repeat the installation of the screws in the holes centered between two blade cutouts for the remaining areas. 6 Tighten the screw(s) until snug. 7 Install the remaining screws in the remaining holes. 8 Tighten the screws until snug. INSTALLATION AND REMOVAL Page 3-60 Rev. 22 Jul/16

153 (This page is intentionally blank.) INSTALLATION AND REMOVAL Page 3-61 Rev. 21 Mar/15

154 C. Installing a Two-Piece Spinner Dome (Procedure 1) (1) General (a) A spinner dome that is installed using Procedure 1 may be identified by the lock nut A at the top of the cylinder. The lock nut A will have a step facing away from the cylinder as illustrated in Figure Lock nut A may have drilled holes for safety wire, but safety wire is not required in this location. (b) The following instructions relate to Hartzell Propeller Inc. spinners only. In some cases, the airframe manufacturer produced the spinner assembly. If so, refer to the airframe manufacturer s manual for spinner installation instructions. SPINNER DOME LOCK NUT B LOCK NUT A (with step) CYLINDER APS6179 Two-Piece Spinner Mounting (Procedure 1) Figure 3-14 INSTALLATION AND REMOVAL Page 3-62 Rev. 21 Mar/15

155 (2) Procedure - Refer to Figure (a) Install the spinner dome. (b) Push the spinner dome toward the bulkhead to align the spinner mounting holes with those of the bulkhead. (c) Using the supplied screws and washers, attach the spinner dome to the spinner bulkhead. Refer to Table Install a screw in each of the one or two holes centered between two blade cutouts. 2 Tighten the screw(s) until snug. 3 Install a screw in each of the one or two holes centered between two blade cutouts on the opposite side of the spinner dome. 4 Tighten the screw(s) until snug. 5 Repeat the installation of the screws in the holes centered between two blade cutouts for the remaining areas. 6 Tighten the screw(s) until snug. 7 Install the remaining screws in the remaining holes. 8 Tighten the screws until snug. (d) Install the lock nut B on the low pitch stop. Refer to Table 3-1 and Figure 3-1 for lock nut torque. (e) Safety wire the lock nut B to each of the two screws on the flat face of the spinner dome surrounding the lock nut B. CAUTION: MAKE SURE THAT THE SCREWS DO NOT EXTEND MORE THAN THREE THREADS PAST THE BULKHEAD NUTPLATES. IF THE SCREWS EXTEND MORE THAN THREE THREADS, THIS CAN CAUSE DAMAGE TO THE AIRCRAFT COWLING. (f) Using flat head screws, attach the spinner dome cap to the spinner dome. Refer to Table 3-5. INSTALLATION AND REMOVAL Page 3-63 Rev. 22 Jul/16

156 APS6161 LOCK NUT A (flat faced) SPINNER DOME LOCK NUT B CYLINDER SPACERS HARTZELL PROPELLER INC. PART NUMBER A (8 MAXIMUM) Two-Piece Spinner Mounting (Procedure 2) Figure 3-15 APS6162 HOLE IN BULKHEAD HOLE IN SPINNER DOME FRONT OF AIRCRAFT (OR REAR FOR PUSHER) Spinner Dome to Bulkhead Mounting Hole Alignment Figure 3-16 INSTALLATION AND REMOVAL Page 3-64 Rev. 21 Mar/15

157 D. Installing a Two-Piece Spinner Dome (Procedure 2) (1) General (a) A spinner dome that is installed using Procedure 2 may identified by the lock nut A at the top of the cylinder. The lock nut will be flat-faced. Refer to Figure Lock nut A may have drilled holes for safety wire, but safety wire is not required in this location. (b) The following instructions relate to Hartzell Propeller Inc. spinners only. In some cases, the airframe manufacturer produced the spinner assembly. If so, refer to the airframe manufacturer s manual for spinner installation instructions. (2) Procedure - Refer to Figure 3-15 (a) Put spacers on the low pitch stop lock nut A. Up to eight spacers may be used. (b) Install spacers, then examine the spinner fit. The spinner is correctly spaced when the holes in the spinner dome are misaligned 1/4-1/3 of their diameter toward the front of the aircraft, or rear in a pusher installation. Refer to Figure Add or remove spacers to achieve this alignment. (c) Install spinner dome. (d) Push the spinner dome aft to align the spinner mounting holes with those of the bulkhead or adapter ring. INSTALLATION AND REMOVAL Page 3-65 Rev. 22 Jul/16

158 CAUTION: MAKE SURE THAT THE SCREWS DO NOT EXTEND MORE THAN THREE THREADS PAST THE BULKHEAD NUTPLATES. IF THE SCREWS EXTEND MORE THAN THREE THREADS, THIS CAN CAUSE DAMAGE TO THE AIRCRAFT COWLING. (e) Using the supplied screws and washers, attach the spinner dome to the spinner bulkhead. Refer to Table Install a screw in each of the one or two holes centered between two blade cutouts. 2 Tighten the screw(s) until snug. 3 Install a screw in each of the one or two holes centered between two blade cutouts on the opposite side of the spinner dome. 4 Tighten the screw(s) until snug. 5 Repeat the installation of the screws in the holes centered between two blade cutouts for the remaining areas. 6 Tighten the screw(s) until snug. 7 Install the remaining screws in the remaining holes. 8 Tighten the screws until snug. (f) Install the lock nut B (that has a shoulder and safety wire holes) on the low pitch stop. Refer to Table 3-1 and Figure 3-1 for lock nut torque. (g) Safety wire the lock nut to each of the two screws on the flat face of the spinner dome surrounding the lock nut. (h) Using flat head screws, attach the spinner dome cap to the spinner dome. INSTALLATION AND REMOVAL Page 3-66 Rev. 22 Jul/16

159 7. Post-Installation Checks Perform Static RPM Check as outlined in the Testing and Troubleshooting chapter in this manual. 8. Spinner Removal CAUTION: WRAP THE BLADE SHANKS IN SEVERAL LAYERS OF MASKING OR DUCT TAPE BEFORE REMOVING THE SPINNER DOME TO PREVENT DAMAGING THE BLADE AND BLADE PAINT. A. Removal of One-Piece Spinner (1) Remove the screws and washers that attach the spinner to the spinner bulkhead or adapter ring. (2) Remove the spinner dome. B. Removal of Two-Piece Spinner (1) Remove the flat head screws that attach the spinner dome cap to the spinner dome. (2) Cut and remove the lock nut safety wire. (3) Remove the lock nut. (4) Remove the screws and washers that attach the spinner dome to the spinner bulkhead. (5) Remove the spinner dome. C. Hub Mounted Spinner Bulkhead Removal (1) Remove propeller. Refer to Propeller Removal in this chapter. (2) Remove the flat washers and self-locking nuts that attach the spinner bulkhead to the propeller hub. Remove the spinner bulkhead. (3) Reinstall the flat washers and self-locking nuts that were removed during the spinner bulkhead removal. D. Starter Ring Gear Spinner Adapter Removal (1) Remove propeller. Refer to Propeller Removal in this chapter. (2) Remove the spinner adapter by removing the hardware that attaches the spinner adapter to the starter ring gear. INSTALLATION AND REMOVAL Page 3-67 Rev. 21 Mar/15

160 9. Propeller Removal A. Removal of D Flange Propellers Propeller Owner's Manual (1) Remove the spinner dome in accordance with the Spinner Removal procedures in this chapter. (2) If the propeller is equipped with an ice protection system that uses components supplied by Hartzell Propeller Inc., applicable instructions and technical information for the components supplied by Hartzell Propeller Inc. can be found in the following publications available on the Hartzell Propeller Inc. website at (a) Hartzell Propeller Inc. Manual 180 ( ) - Propeller Ice Protection System Manual (b) Hartzell Propeller Inc. Manual 181 ( ) - Propeller Ice Protection System Component Maintenance Manual (c) Hartzell Propeller Inc. Manual 182 ( ) - Propeller Electrical De-Ice Boot Removal and Installation Manual (d) Hartzell Propeller Inc. Manual 183 ( ) - Propeller Anti-Icing Boot Removal and Installation Manual (3) Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by the applicable TC or STC holder s Instructions for Continued Airworthiness (ICA). (4) If installed, cut and remove the safety wire or safety cable on the propeller mounting studs. WARNING: MAKE SURE THE SLING IS RATED UP TO 800 LBS. (363 KG) TO SUPPORT THE WEIGHT OF THE PROPELLER ASSEMBLY DURING REMOVAL. (5) Support the propeller assembly with a sling. NOTE: Supporting the propeller with the sling may be delayed until all but two mounting nuts and spacers have been removed. INSTALLATION AND REMOVAL Page 3-68 Rev. 21 Mar/15

161 (6) If the propeller will be reinstalled and it has been dynamically balanced, make an identifying mark (with a felt-tipped pen only) on the propeller hub and a matching mark on the engine flange to make sure of correct positioning of the propeller during re-installation. NOTE: This will prevent dynamic imbalance. CAUTION: DISCARD THE PROPELLER MOUNTING NUTS AND SPACERS IF THEY ARE DAMAGED OR CORRODED, OR WHEN THE PROPELLER IS REMOVED FOR OVERHAUL. (7) Remove the eight 1/2 inch mounting nuts. (a) If the propeller is removed between overhaul intervals, mounting studs, nuts, and spacers may be reused if they are not damaged or corroded. CAUTION: REMOVE THE PROPELLER FROM THE MOUNTING FLANGE WITH CARE TO PREVENT DAMAGING THE PROPELLER MOUNTING STUDS. (8) Using the support sling, remove the propeller from the mounting flange. (9) Put the propeller on a cart for transport. INSTALLATION AND REMOVAL Page 3-69 Rev. 21 Mar/15

162 B. Removal of F Flange Propellers Propeller Owner's Manual (1) Remove the spinner dome in accordance with the Spinner Removal procedures in this chapter. (2) If the propeller is equipped with an ice protection system that uses components supplied by Hartzell Propeller Inc., applicable instructions and technical information for the components supplied by Hartzell Propeller Inc. can be found in the following publications available on the Hartzell Propeller Inc. website at (a) Hartzell Propeller Inc. Manual 180 ( ) - Propeller Ice Protection System Manual (b) Hartzell Propeller Inc. Manual 181 ( ) - Propeller Ice Protection System Component Maintenance Manual (c) Hartzell Propeller Inc. Manual 182 ( ) - Propeller Electrical De-Ice Boot Removal and Installation Manual (d) Hartzell Propeller Inc. Manual 183 ( ) - Propeller Anti-Icing Boot Removal and Installation Manual (3) Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by the applicable TC or STC holder s Instructions for Continued Airworthiness (ICA). (4) If installed, cut and remove the safety wire or safety cable on the propeller mounting studs. WARNING: MAKE SURE THE SLING IS RATED UP TO 800 LBS. (363 KG) TO SUPPORT THE WEIGHT OF THE PROPELLER ASSEMBLY DURING REMOVAL. (5) Support the propeller assembly with a sling. NOTE: Supporting the propeller with the sling may be delayed until all but two mounting nuts and washers have been removed. INSTALLATION AND REMOVAL Page 3-70 Rev. 21 Mar/15

163 (6) If the propeller will be reinstalled and it has been dynamically balanced, make an identifying mark (with a felt-tipped pen only) on the propeller hub and a matching mark on the engine flange to make sure of correct positioning of the propeller during re-installation. NOTE: This will prevent dynamic imbalance. CAUTION: DISCARD THE PROPELLER MOUNTING NUTS AND WASHERS IF THEY ARE DAMAGED OR CORRODED, OR WHEN THE PROPELLER IS REMOVED FOR OVERHAUL. (7) Remove the six 1/2 inch mounting nuts. (a) If the propeller is removed between overhaul intervals, mounting studs, nuts and washers may be reused if they are not damaged or corroded. CAUTION: REMOVE THE PROPELLER FROM THE MOUNTING FLANGE WITH CARE TO PREVENT DAMAGING THE PROPELLER MOUNTING STUDS. (8) Using the support sling, remove the propeller from the mounting flange. (9) Put the propeller on a cart for transport. INSTALLATION AND REMOVAL Page 3-71 Rev. 21 Mar/15

164 C. Removal of N Flange Propellers Propeller Owner's Manual (1) Remove the spinner dome in accordance with the Spinner Removal procedures in this chapter. (2) If the propeller is equipped with an ice protection system that uses components supplied by Hartzell Propeller Inc., applicable instructions and technical information for the components supplied by Hartzell Propeller Inc. can be found in the following publications available on the Hartzell Propeller Inc. website at (a) Hartzell Propeller Inc. Manual 180 ( ) - Propeller Ice Protection System Manual (b) Hartzell Propeller Inc. Manual 181 ( ) - Propeller Ice Protection System Component Maintenance Manual (c) Hartzell Propeller Inc. Manual 182 ( ) - Propeller Electrical De-Ice Boot Removal and Installation Manual (d) Hartzell Propeller Inc. Manual 183 ( ) - Propeller Anti-Icing Boot Removal and Installation Manual (3) Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by the applicable TC or STC holder s Instructions for Continued Airworthiness (ICA). (4) If installed, cut and remove the safety wire or safety cable on the propeller mounting studs. WARNING: MAKE SURE THE SLING IS RATED UP TO 800 LBS. (363 KG) TO SUPPORT THE WEIGHT OF THE PROPELLER ASSEMBLY DURING REMOVAL. (5) Support the propeller assembly with a sling. NOTE: Supporting the propeller with the sling may be delayed until all but two mounting studs and washers have been removed. INSTALLATION AND REMOVAL Page 3-72 Rev. 21 Mar/15

165 (6) If the propeller will be reinstalled and it has been dynamically balanced, make an identifying mark (with a felt-tipped pen only) on the propeller hub and a matching mark on the engine flange to make sure of correct positioning of the propeller during re-installation. NOTE: This will prevent dynamic imbalance. CAUTION: DISCARD THE PROPELLER MOUNTING NUTS AND WASHERS IF THEY ARE DAMAGED OR CORRODED, OR WHEN THE PROPELLER IS REMOVED FOR OVERHAUL. (7) Remove the eight 9/16 inch mounting nuts. (a) If the propeller is removed between overhaul intervals, mounting studs, nuts and washers may be reused if they are not damaged or corroded. CAUTION: REMOVE THE PROPELLER FROM THE ENGINE MOUNTING FLANGE WITH CARE TO PREVENT DAMAGING THE PROPELLER MOUNTING STUDS. (8) Using the support sling, remove the propeller from the mounting flange. (9) Put the propeller on a cart for transport. INSTALLATION AND REMOVAL Page 3-73 Rev. 21 Mar/15

166 D. Removal of L Flange Propellers, Except Model HC-E2YL-( ) (1) Remove the spinner dome in accordance with the Spinner Removal procedures in this chapter. (2) If the propeller is equipped with an ice protection system that uses components supplied by Hartzell Propeller Inc., applicable instructions and technical information for the components supplied by Hartzell Propeller Inc. can be found in the following publications available on the Hartzell Propeller Inc. website at (a) Hartzell Propeller Inc. Manual 180 ( ) - Propeller Ice Protection System Manual (b) Hartzell Propeller Inc. Manual 181 ( ) - Propeller Ice Protection System Component Maintenance Manual (c) Hartzell Propeller Inc. Manual 182 ( ) - Propeller Electrical De-Ice Boot Removal and Installation Manual (d) Hartzell Propeller Inc. Manual 183 ( ) - Propeller Anti-Icing Boot Removal and Installation Manual (3) Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by the applicable TC or STC holder s Instructions for Continued Airworthiness (ICA). (4) If installed, cut and remove the safety wire or safety cable on the propeller mounting stud nuts. WARNING: MAKE SURE THE SLING IS RATED UP TO 800 LBS. (363 KG) TO SUPPORT THE WEIGHT OF THE PROPELLER ASSEMBLY DURING REMOVAL. (5) Support the propeller assembly with a sling. (6) If the propeller will be reinstalled and it has been dynamically balanced, make an identifying mark (with a felt-tipped pen only) on the propeller hub and a matching mark on the engine flange to make sure of correct positioning of the propeller during re-installation. NOTE: This will prevent dynamic imbalance. INSTALLATION AND REMOVAL Page 3-74 Rev. 21 Mar/15

167 CAUTION: DISCARD THE PROPELLER MOUNTING STUDS, NUTS, AND WASHERS IF THEY ARE DAMAGED OR CORRODED, OR WHEN THE PROPELLER IS REMOVED FOR OVERHAUL. (7) Unscrew the six 7/16 inch mounting studs from the engine bushings. (a) If the propeller is removed between overhaul intervals, mounting studs, nuts and washers may be reused if they are not damaged or corroded. CAUTION: REMOVE THE PROPELLER FROM THE ENGINE MOUNTING FLANGE WITH CARE TO PREVENT DAMAGING THE PROPELLER MOUNTING STUDS. (8) Using the support sling, remove the propeller from the mounting flange. (9) Put the propeller on a cart for transport. INSTALLATION AND REMOVAL Page 3-75 Rev. 21 Mar/15

168 E. Removal of HC-E2YL-( ) Propellers Propeller Owner's Manual (1) Remove the spinner dome in accordance with the Spinner Removal procedures in this chapter. (2) If the propeller is equipped with an ice protection system that uses components supplied by Hartzell Propeller Inc., applicable instructions and technical information for the components supplied by Hartzell Propeller Inc. can be found in the following publications available on the Hartzell Propeller Inc. website at (a) Hartzell Propeller Inc. Manual 180 ( ) - Propeller Ice Protection System Manual (b) Hartzell Propeller Inc. Manual 181 ( ) - Propeller Ice Protection System Component Maintenance Manual (c) Hartzell Propeller Inc. Manual 182 ( ) - Propeller Electrical De-Ice Boot Removal and Installation Manual (d) Hartzell Propeller Inc. Manual 183 ( ) - Propeller Anti-Icing Boot Removal and Installation Manual (3) Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by the applicable TC or STC holder s Instructions for Continued Airworthiness (ICA). (4) If installed, cut and remove the safety wireor safety cable on the propeller mounting stud nuts. WARNING: MAKE SURE THE SLING IS RATED UP TO 800 LBS. (363 KG) TO SUPPORT THE WEIGHT OF THE PROPELLER ASSEMBLY DURING REMOVAL. (5) Support the propeller assembly with a sling. (6) If the propeller will be reinstalled and it has been dynamically balanced, make an identifying mark (with a felt-tipped pen only) on the propeller hub and a matching mark on the engine flange to make sure of correct positioning of the propeller during re-installation. NOTE: This will prevent dynamic imbalance. INSTALLATION AND REMOVAL Page 3-76 Rev. 21 Mar/15

169 CAUTION: DISCARD THE PROPELLER MOUNTING STUDS, NUTS, OR BOLTS IF THEY ARE DAMAGED OR CORRODED, OR WHEN THE PROPELLER IS REMOVED FOR OVERHAUL. (7) Unscrew the four 7/16 inch mounting bolts from the engine bushings. (8) Unscrew the two 7/16 inch mounting nuts and the attached studs from the engine bushings. (a) If the propeller is removed between overhaul intervals, mounting studs, nuts and washers may be reused if they are not damaged or corroded. CAUTION: REMOVE THE PROPELLER FROM THE MOUNTING FLANGE WITH CARE TO PREVENT DAMAGING THE PROPELLER MOUNTING STUDS. (9) Using the support sling, remove the propeller from the mounting flange. (10) Put the propeller on a cart for transport. INSTALLATION AND REMOVAL Page 3-77 Rev. 21 Mar/15

170 F. Removal of K and R Flange Propellers (1) Remove the spinner dome in accordance with the Spinner Removal procedures in this chapter. (2) If the propeller is equipped with an ice protection system that uses components supplied by Hartzell Propeller Inc., applicable instructions and technical information for the components supplied by Hartzell Propeller Inc. can be found in the following publications available on the Hartzell Propeller Inc. website at (a) Hartzell Propeller Inc. Manual 180 ( ) - Propeller Ice Protection System Manual (b) Hartzell Propeller Inc. Manual 181 ( ) - Propeller Ice Protection System Component Maintenance Manual (c) Hartzell Propeller Inc. Manual 182 ( ) - Propeller Electrical De-Ice Boot Removal and Installation Manual (d) Hartzell Propeller Inc. Manual 183 ( ) - Propeller Anti-Icing Boot Removal and Installation Manual (3) Propeller ice protection system components not supplied by Hartzell Propeller Inc. are controlled by the applicable TC or STC holder s Instructions for Continued Airworthiness (ICA). (4) If installed, cut and remove the safety wire or safety cable on the propeller mounting stud nuts. WARNING: MAKE SURE THE SLING IS RATED UP TO 800 LBS. (363 KG) TO SUPPORT THE WEIGHT OF THE PROPELLER ASSEMBLY DURING REMOVAL. (5) Support the propeller assembly with a sling. (6) If the propeller will be reinstalled and it has been dynamically balanced, make an identifying mark (with a felt-tipped pen only) on the propeller hub and a matching mark on the engine flange to make sure of correct positioning of the propeller during re-installation. NOTE: This will prevent dynamic imbalance. INSTALLATION AND REMOVAL Page 3-78 Rev. 21 Mar/15

171 CAUTION: DISCARD THE PROPELLER MOUNTING STUDS, NUTS, AND WASHERS IF THEY ARE DAMAGED OR CORRODED, OR WHEN THE PROPELLER IS REMOVED FOR OVERHAUL. (7) Unscrew the six 1/2 inch mounting studs from the engine bushings. (a) If the propeller is removed between overhaul intervals, mounting studs, nuts and washers may be reused if they are not damaged or corroded. CAUTION: REMOVE THE PROPELLER FROM THE MOUNTING FLANGE WITH CARE TO PREVENT DAMAGING THE PROPELLER MOUNTING STUDS. (8) Using the support sling, remove the propeller from the mounting flange. (9) Put the propeller on a cart for transport. INSTALLATION AND REMOVAL Page 3-79 Rev. 21 Mar/15

172 (This page is intentionally blank.) INSTALLATION AND REMOVAL Page 3-80 Rev. 21 Mar/15

173 TESTING AND TROUBLESHOOTING - CONTENTS 1. Operational Tests A. General B. Initial Run-Up C. Static RPM Check D. Post-Run Check Propeller Ice Protection Systems A. Electric De-ice System B. Anti-ice System Troubleshooting A. Hunting and Surging B. Engine Speed Varies with Flight Attitude (Airspeed) C. Loss of Propeller Control (-1 propellers only) D. Loss of Propeller Control (-2, -4 or -5 propellers) E. Failure to Feather or Feathers Slowly (-2 or -5 propellers only) F. Failure to Unfeather G. Start Locks (Anti-feather Latches) Fail to Latch on Shutdown (-2 and some -5 feathering propellers only) H. Vibration I. Propeller Overspeed J. Propeller Underspeed K. Oil or Grease Leakage TESTING AND TROUBLESHOOTING Page 4-1 Rev. 20 Mar/14

174 (This page is intentionally blank.) TESTING AND TROUBLESHOOTING Page 4-2 Rev. 20 Mar/14

175 1. Operational Tests CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS SECTION MAY INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS. REFER TO THE ILLUSTRATED PARTS LIST CHAPTER OF THE APPLICABLE OVERHAUL MANUAL(S) FOR THE IDENTIFICATION OF SPECIFIC PROPELLER CRITICAL PARTS. A. General (1) The propeller must be installed on an application using a propeller governor. (2) Perform the test after propeller installation and before every flight. (3) The propeller system must be purged of air and correct operation verified. B. Initial Run-Up (1) Perform engine start and warm-up per the Pilot's Operating Handbook (POH). CAUTION: AIR TRAPPED IN THE PROPELLER HYDRAULIC SYSTEM WILL CAUSE THE PITCH CONTROL TO BE IMPRECISE AND MAY RESULT IN PROPELLER SURGING. (2) Cycle the propeller control throughout its operating range from low to high (or as directed by the POH). (3) Repeat this procedure at least three times to purge air from the propeller hydraulic system and to introduce warmed oil to the cylinder. NOTE: Pitch change response on the first operation from low to high blade pitch may be slow, but should speed up on the second and third cycles. (4) Verify proper operation from low pitch to high pitch and throughout operating range. (5) Shut down the engine in accordance with the POH. TESTING AND TROUBLESHOOTING Page 4-3 Rev. 20 Mar/14

176 C. Static RPM Check NOTE: Propeller Owner's Manual This operational check should be performed after installation, maintenance, or propeller adjustment. CAUTION: A CALIBRATED TACHOMETER MUST BE USED TO MAKE SURE OF THE ACCURACY OF THE RPM CHECK. (1) Set the brakes and chock the aircraft or tie aircraft down. (2) Back the governor Maximum RPM Stop out one turn. (3) Start the engine. (4) Advance the propeller control lever to MAX (max RPM), then retard the control lever one inch (25.4 mm). (5) SLOWLY advance the throttle to maximum manifold pressure. (6) Slowly advance the propeller control lever until the engine speed stabilizes. (a) If engine speed stabilizes at the maximum power static RPM specified by the TC or STC holder, then the low pitch stop is set correctly. (b) If engine speed stabilizes above or below the rated RPM, the low pitch stop may require adjustment. Refer to the Maintenance Practices chapter of this manual. (7) Stop the engine. (8) Return the governor Maximum RPM Stop to the original position, or adjust the governor to the rated RPM with the Maximum RPM Stop screw. (a) If the governor is adjusted to the rated RPM with the maximum RPM stop screw, hold the maximum RPM stop screw in place and torque the maximum RPM stop locking nut in accordance with Table 3-1, Torque Table. CAUTION: REFER TO THE AIRCRAFT MAINTENANCE MANUAL FOR ADDITIONAL PROCEDURES THAT MAY BE REQUIRED AFTER PROPELLER INSTALLATION. D. Post-Run Check (1) After engine shutdown, check propeller for signs of engine oil leakage. TESTING AND TROUBLESHOOTING Page 4-4 Rev. 20 Mar/14

177 2. Propeller Ice Protection Systems A. Electric De-ice System Propeller Owner's Manual (1) Consult the Pilot Operating Handbook (including all supplements) regarding flight into conditions of known icing. The aircraft may not be certificated for flight in known icing conditions, even though propeller de-ice equipment is installed. (2) Refer to the Anti-ice and De-ice Systems chapter of this manual for functional tests of the de-ice system. B. Anti-ice System (1) Consult the Pilot Operating Handbook (including all supplements) regarding flight into conditions of known icing. The aircraft may not be certificated for flight in known icing conditions, even though propeller anti-ice equipment is installed. (2) Refer to the Anti-ice and De-ice Systems Chapter of this manual for functional tests of the anti-ice system. TESTING AND TROUBLESHOOTING Page 4-5 Rev. 14 Jan/09

178 3. Troubleshooting CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS SECTION MAY INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS. REFER TO THE ILLUSTRATED PARTS LIST CHAPTER OF THE APPLICABLE OVERHAUL MANUAL(S) FOR THE IDENTIFICATION OF SPECIFIC PROPELLER CRITICAL PARTS. A. Hunting and Surging Hunting is characterized by a cyclic variation in engine speed above and below desired speed. Surging is characterized by a large increase/decrease in engine speed, followed by a return to set speed after one or two occurrences. (1) If propeller is hunting, an appropriately licensed repair facility should check: (a) Governor (b) Fuel control (c) Synchrophaser or synchronizer (2) If propeller is surging: Perform Steps 1.A.(1)-1.A.(5) under "Operational Tests," in this chapter to release trapped air from the propeller. If surging recurs, it is most likely due to a faulty governor. Have the governor tested by an appropriately licensed propeller repair facility. (3) Hunting and/or surging may also be caused by friction or binding within the governor control, or by internal propeller corrosion, which causes the propeller to react slower to governor commands. The propeller must be tested at an appropriately licensed propeller repair facility to isolate these faults. B. Engine Speed Varies with Flight Attitude (Airspeed) (1) Small variances in engine speed are normal and are no cause for concern. TESTING AND TROUBLESHOOTING Page 4-6 Rev. 17 Jul/12

179 (2) Increase in engine speed while descending or increasing airspeed: (a) Non-feathering (-1) propeller: 1 Governor is not increasing oil volume in the propeller. 2 Engine transfer bearing is leaking excessively. 3 Excessive friction in blade bearings or pitch changing mechanism. (b) Feathering (-2, -5) or Aerobatic (-4) propeller: 1 Governor is not reducing oil volume in propeller. 2 Air charge (-2, -5) too low. Refer to Air Charge in the Maintenance Practices chapter of this manual. 3 Excessive friction in blade bearings or pitch changing mechanism. (3) Decrease in engine speed while increasing airspeed: (a) Non-feathering (-1) propeller: 1 Governor pilot valve is stuck and is excessively increasing oil volume. (b) Feathering (-2, -5) or Aerobatic (-4) propeller: 1 Governor pilot valve is stuck and is excessively decreasing oil volume. 2 Feathering command engaged on propeller pitch control (-2, -5 propeller only). (4) Increase in engine speed while decreasing airspeed: (a) Non-feathering (-1) propeller: 1 Governor pilot valve is stuck and is excessively decreasing oil volume. (b) Feathering (-2, -5) or Aerobatic (-4) propeller: 1 Governor pilot valve is stuck and is excessively increasing oil volume. (5) Decrease in engine speed while decreasing airspeed: (a) Non-feathering (-1) propeller: 1 Governor is not reducing oil volume in propeller. 2 Excessive friction in blade bearings or pitch changing mechanism. TESTING AND TROUBLESHOOTING Page 4-7 Rev. 14 Jan/09

180 (b) Feathering (-2, -5) or Aerobatic (-4) propeller: 1 Governor is not increasing oil volume in propeller. 2 Air charge (-2, -5) too high. Refer to Air Charge in the Maintenance Practices chapter of this manual. 3 Engine transfer bearing leaking excessively. 4 Excessive friction in blade bearings or pitch changing mechanism. C. Loss of Propeller Control (-1 propellers only) (1) Propeller goes to uncommanded Low Pitch (High RPM) (a) Loss of propeller oil pressure - Check: 1 Governor pressure relief valve for proper operation 2 Governor drive for damage 3 Adequate engine oil supply 4 Engine transfer bearing leaking excessively (2) Propeller goes to uncommanded High Pitch (Low RPM) (a) Governor pilot valve sticking (3) RPM Increases with Power and Airspeed, Propeller RPM Control has Little or No Effect (a) Excessive friction in blade bearings or pitch changing mechanism (b) Internal oil leakage to opposite side of piston and into hub D. Loss of Propeller Control (-2, -4 or -5 propellers) (1) Propeller goes to uncommanded High Pitch (or Feather) (a) Loss of propeller oil pressure - Check: 1 Governor pressure relief valve for proper operation 2 Governor drive for damage 3 Adequate engine oil supply 4 Engine transfer bearing leaking excessively (b) Start locks not engaging (-2, -5) (c) Air charge pressure too high (-2, -5). Refer to Air Charge in the Maintenance Practices chapter of this manual. TESTING AND TROUBLESHOOTING Page 4-8 Rev. 17 Jul/12

181 (2) Propeller goes to uncommanded Low Pitch (High RPM) (a) Governor pilot valve sticking (3) RPM Increases with Power and Airspeed, Propeller RPM Control has Little or No Effect (a) Excessive friction in blade bearings or pitch changing mechanism. (b) Air charge lost or low. (-2, -5). Refer to the Air Charge section in the Maintenance Practices chapter of this manual. (c) Broken feathering spring (-2, -5). (4) RPM Control Sluggish (a) Air charge lost or low (-2, -5). Refer to the Air Charge section in the Maintenance Practices chapter of this manual. E. Failure to Feather or Feathers Slowly (-2 or -5 propellers only) (1) Air charge lost or low. Refer to the Air Charge section in the Maintenance Practices chapter of this manual. (2) Check for proper function and rigging of propeller/ governor control linkage. (3) Check governor drain function. (4) Check the propeller for misadjustment or internal corrosion (usually in blade bearings or pitch change mechanism) that results in excessive friction. This must be performed at an appropriately licensed propeller repair facility. F. Failure to Unfeather (1) Check for proper function and rigging of propeller control linkage. (2) Perform a check of the governor function, including the unfeathering accumulator, if applicable. (3) Check for excessive oil leakage at engine transfer bearing. TESTING AND TROUBLESHOOTING Page 4-9 Rev. 17 Jul/12

182 (4) Check the propeller for misadjustment or internal corrosion (usually in blade bearings or pitch change mechanism) that results in excessive friction. This check must be performed at an appropriately licensed propeller repair facility. G. Start Locks (Anti-feather Latches) Fail to Latch on Shutdown (-2 and some -5 feathering propellers only) (1) Propeller was feathered before shutdown. (2) Shutdown occurred at high RPM with prop control off the low pitch stop. (3) Air charge too high (-2, -5). Refer to Air Charge in the Maintenance Practices chapter of this manual. (4) Excessive engine transfer bearing oil leakage. (5) Excessive governor pump leakage. (6) Broken start locks. Problems G(1) and G(2) above may be solved by restarting the engine, placing the propeller control in the proper shutdown position, and then shutting down the engine. Problems G(4), G(5), and G(6) should be referred to an appropriately licensed propeller repair facility. TESTING AND TROUBLESHOOTING Page 4-10 Rev. 17 Jul/12

183 H. Vibration CAUTION 1: ANY VIBRATION THAT OCCURS SUDDENLY, OR IS ACCOMPANIED BY UNEXPLAINED GREASE LEAKAGE SHOULD BE INVESTIGATED IMMEDIATELY BEFORE FURTHER FLIGHT. CAUTION 2: VIBRATION PROBLEMS BECAUSE OF PROPELLER SYSTEM IMBALANCE ARE NORMALLY FELT THROUGHOUT THE RPM RANGE, WITH THE INTENSITY OF VIBRATION INCREASING WITH RPM. VIBRATION PROBLEMS THAT OCCUR IN A NARROW RPM RANGE ARE A SYMPTOM OF RESONANCE, THAT IS POTENTIALLY HARMFUL TO THE PROPELLER. AVOID OPERATION UNTIL THE PROPELLER CAN BE CHECKED BY AN APPROPRIATELY LICENSED REPAIR FACILITY. (1) Check: (a) Control surfaces, cowl flaps, exhaust system, landing gear doors, etc. for excessive play, which may be causing vibration unrelated to the propeller. (b) Secure attachment of engine mounted hardware. (c) Engine mount wear. (d) Uneven or over lubrication of propeller. (e) Proper engine/propeller flange mating. (f) Blade track. Refer to Blade Track in the Inspection and Check chapter of this manual. (g) Blade angles: Blade angle must be within 0.2 degree from blade to blade. (h) Spinner for cracks, improper installation, or "wobble" during operation. (i) Static balance. TESTING AND TROUBLESHOOTING Page 4-11 Rev. 14 Jan/09

184 (j) Airfoil profile identical between blades. After overhaul or rework for nicks - verify at appropriately licensed propeller repair facility. (k) Propeller installation - remove and reinstall propeller 180 degrees from original installation position. 1 "R" flange propellers installed on an "R" engine flange cannot be reinstalled 180 degrees from original installation position. (l) Hub or blade damage or cracking. (m) Grease or oil leakage. (n) Bends or blade deformation. NOTE: Dynamic balancing is recommended after installing or performing maintenance on a propeller. While normally an optional task, it may be required by the engine or airframe manufacturer to make certain the propeller/ engine combination is balanced correctly before operation. Refer to the engine or airframe manuals, and the Maintenance Practices chapter of this manual. I. Propeller Overspeed (1) Check: (a) Tachometer error (b) Low pitch stop adjustment (c) Governor maximum RPM set too high (d) Loss of oil pressure (-1 propellers) 1 Oil starvation 2 Governor failure (e) Loss or lowered air charge (-2 or -5 propellers - results in momentary overspeed). Refer to the Air Charge section in the Maintenance Practices chapter of this manual. (f) Governor pilot valve jammed to supply high pressure only (-2, -4 or -5 propellers) (g) Oil leaking past piston causing hydraulic lock of piston in cylinder (-1 propellers) TESTING AND TROUBLESHOOTING Page 4-12 Rev. 14 Jan/09

185 J. Propeller Underspeed (1) Check: (a) Tachometer error. Propeller Owner's Manual (b) Excessive transfer bearing oil leakage (-2, -4, or -5 propellers). (c) Governor oil pressure low (-2, -4, or -5 propellers). (d) Governor oil passage clogged. (e) Oil leaking past piston causing hydraulic lock in cylinder (-2, -4, or -5 propellers). K. Oil or Grease Leakage NOTE: A new propeller may leak grease slightly during the first several hours of operation. This leakage may be caused by the seating of seals and O-rings, and the slinging of lubricants used during assembly. Such leakage should stop within the first ten hours of operation. CAUTION: GREASE LEAKAGE THAT CAN BE DESCRIBED AS EXCESSIVE AND APPEARING SUDDENLY, ESPECIALLY WHEN ACCOMPANIED BY VIBRATION SHOULD BE INVESTIGATED IMMEDIATELY BEFORE FURTHER FLIGHT. (1) Check: (a) Improperly torqued or loose lubrication fitting. (b) Defective lubrication fitting. (c) Damaged blade shank to hub O-ring seal. (d) Damaged hub seal (at hub parting line). (e) Damaged engine transfer O-ring at hub/engine flange interface. (f) Cracked hub. A cracked hub is often indicated by grease emerging from a seemingly solid surface, especially in the blade arm area. TESTING AND TROUBLESHOOTING Page 4-13 Rev. 14 Jan/09

186 (This page is intentionally blank.) TESTING AND TROUBLESHOOTING Page 4-14 Rev. 14 Jan/09

187 Propeller Owner s Manual INSPECTION AND CHECK - CONTENTS 1. Pre-Flight Checks Post-Flight Checks A. HC-C2YR-2CLUF/FLC7666A-4 Propellers Installed on OMA SUD Skycar Aircraft Operational Checks Required Periodic Inspections and Maintenance A. Periodic Inspections B Blade Inspection for an HC-C2YR-2CLUF/FLC7666A-4 Propeller Installed on OMA SUD Skycar Aircraft C. Spinner Bulkhead Inspection for an HC-E3YR-1RF Propeller Installed on S.N.A. Inc. Seawind Aircraft D. Low Pitch Stop Hardware Inspection for a PHC-C3YF-2UF/FC7693DFB Propeller E. Periodic Maintenance F. Airworthiness Limitations G. Overhaul Periods Inspection Procedures A. Blade Damage B. Grease or Oil Leakage C. Vibration D. Tachometer Inspection E. Blade Track F. Loose Blades G. Corrosion H. Spinner Damage I. Electric De-ice System J. Anti-ice System Special Inspections A. Overspeed/Overtorque B. Lightning Strike C. Foreign Object Strike D. Fire Damage or Heat Damage Long Term Storage INSPECTION AND CHECK Page 5-1 Rev. 22 Jul/16

188 Propeller Owner s Manual LIST OF FIGURES Checking Blade Track... Figure Blade Play... Figure Reciprocating Engine Overspeed Limits... Figure Turbine Engine Overspeed Limits... Figure Turbine Engine Overtorque Limits... Figure INSPECTION AND CHECK Page 5-2 Rev. 22 Jul/16

189 Propeller Owner s Manual 1. Pre-Flight Checks CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS SECTION MAY INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS. REFER TO THE ILLUSTRATED PARTS LIST CHAPTER OF THE APPLICABLE OVERHAUL MANUAL(S) FOR THE IDENTIFICATION OF SPECIFIC PROPELLER CRITICAL PARTS. Follow propeller preflight inspection procedures as specified in the Pilot Operating Handbook (POH). In addition, perform the following inspections: A. Blades (1) Visually inspect the entire blade (lead, trail, face, and camber sides) for nicks, gouges, and cracks. Refer to the Maintenance Practices chapter of this manual, for blade repair information. Normal blade lead edge erosion (sand-blasted appearance) is acceptable, and does not require removal before further flight. (2) Visually inspect the blades for lightning strike. Refer to the Lightning Strike Damage section in this chapter for a description of damage. B. Inspect the spinner and visible blade retention components for damage or cracks. Repair or replace components as required before further flight. C. Check for loose/missing hardware. Retighten or reinstall as necessary. WARNING: ABNORMAL GREASE LEAKAGE CAN BE AN INDICATION OF A FAILING PROPELLER BLADE OR BLADE RETENTION COMPONENT. AN IN-FLIGHT BLADE SEPARATION CAN RESULT IN A CATASTROPHIC AIRCRAFT ACCIDENT. D. Inspect for grease and oil leakage and determine its source. INSPECTION AND CHECK Page 5-3 Rev. 17 Jul/12

190 Propeller Owner s Manual WARNING: ABNORMAL VIBRATION CAN BE AN INDICATION OF A FAILING PROPELLER BLADE OR BLADE RETENTION COMPONENT. AN IN-FLIGHT BLADE SEPARATION CAN RESULT IN A CATASTROPHIC AIRCRAFT ACCIDENT. E. Check the blades for radial play or movement of the blade tip (in and out, fore and aft, and end play). Refer to Loose Blades, in the Periodic Inspections section of this chapter, for blade play limits. F. Inspect the anti-icing or de-ice boots (if installed) for damage. Refer to the Anti-Ice and De-Ice Systems chapter of this manual, for inspection information. G. Refer to the Periodic Inspections section in this chapter for additional inspection information and possible corrections to any discrepancies discovered as a result of preflight checks. 2. Post-Flight Checks CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS SECTION MAY INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS. REFER TO THE ILLUSTRATED PARTS LIST CHAPTER OF THE APPLICABLE OVERHAUL MANUAL(S) FOR THE IDENTIFICATION OF SPECIFIC PROPELLER CRITICAL PARTS. A. HC-C2YR-2CLUF/FLC7666A-4 Propellers Installed on OMA SUD Skycar Aircraft (1) As a result of the pusher configuration, propeller blades on affected aircraft are exposed to hot exhaust gasses, which makes them more susceptible to erosion and corrosion, additional inspections and corrosion preventative measures are required. (a) Perform blade cleaning within three days after any flight. NOTE: It is recommended to perform blade cleaning after the last flight of each day. INSPECTION AND CHECK Page 5-4 Rev. 17 Jul/12

191 (b) Blade Cleaning Propeller Owner s Manual WARNING: CLEANING AGENTS (ACETONE, #700 LACQUER THINNER, AND MEK), ARE FLAMMABLE AND TOXIC TO THE SKIN, EYES, AND RESPIRATORY TRACT. SKIN AND EYE PROTECTION ARE REQUIRED. AVOID PROLONGED CONTACT. USE IN WELL VENTILATED AREA. 1 Using a cloth dampened with actetone, MEK, or MPK, thoroughly clean each blade shank where exposed to engine exhaust and remove all foreign matter/exhaust residue. 2 Visually inspect for corrosion indications and paint condition. 3 Paint must be in good condition in the area exposed to exhaust gasses. Repair and repaint in accordance with the Maintenance Practices chapter of this manual or by an appropriately licensed propeller repair facility if: a Any of the underlying aluminum blade is exposed. b There are any indications of corrosion, such as pitting or any other unusual conditions. 3. Operational Checks CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS SECTION MAY INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS. REFER TO THE ILLUSTRATED PARTS LIST CHAPTER OF THE APPLICABLE OVERHAUL MANUAL(S) FOR THE IDENTIFICATION OF SPECIFIC PROPELLER CRITICAL PARTS. A. Following propeller installation and before flight, perform initial run-up as outlined in Operational Tests in the Testing and Troubleshooting chapter of this manual. INSPECTION AND CHECK Page 5-5 Rev. 17 Jul/12

192 Propeller Owner s Manual B. Check the propeller speed control and operation from reverse or low pitch to high pitch, using the procedure specified in the Pilot Operating Handbook (POH) for the aircraft. (1) Perform all ground functional, feathering, and cycling checks with a minimum propeller RPM drop required to demonstrate function. (2) A typical RPM drop is RPM for feathering propellers and 100 to 300 RPM for non-feathering propellers. WARNING: ABNORMAL VIBRATION CAN BE AN INDICATION OF A FAILING PROPELLER BLADE OR BLADE RETENTION COMPONENT. AN IN-FLIGHT BLADE SEPARATION CAN RESULT IN DEATH, SERIOUS BODILY INJURY, AND/OR SUBSTANTIAL PROPERTY DAMAGE. C. Check for any abnormal vibration during this run-up. If vibration occurs, shut the engine down, determine the cause, and correct it before further flight. Refer to the Vibration section in the Testing and Troubleshooting chapter of this manual. D. Refer to Periodic Inspections in this chapter for additional inspection information and possible corrections to any discrepancies discovered as a result of Pre-Flight Checks. E. Refer to the airframe manufacturer s manual for additional operational checks. INSPECTION AND CHECK Page 5-6 Rev. 17 Jul/12

193 Propeller Owner s Manual 4. Required Periodic Inspections and Maintenance CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS SECTION MAY INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS. REFER TO THE ILLUSTRATED PARTS LIST CHAPTER OF THE APPLICABLE OVERHAUL MANUAL(S) FOR THE IDENTIFICATION OF SPECIFIC PROPELLER CRITICAL PARTS. A. Periodic Inspections Accomplish a detailed inspection at 100 hour intervals not to exceed twelve (12) calendar months. Procedures involved in these inspections are detailed below. NOTE 1: Inspection and maintenance specified by an airframe manufacturer's maintenance program and approved by the applicable airworthiness agency may not coincide with the inspection time intervals specified. In this situation, the airframe manufacturer's schedule may be applied with the exception that the calendar limit for the inspection interval may not exceed twelve (12) months. NOTE 2: Refer to Inspection Procedures in this chapter for additional inspection information and possible corrections to any discrepancies discovered as a result of the Periodic Inspection. (1) Remove the spinner dome. CAUTION: DO NOT ATTEMPT TO REPAIR A CRACKED BLADE. (2) Visually inspect the blades for nicks, gouges, and cracks. If any damage is discovered, refer to the Blade Repairs section in the Maintenance Practices chapter of this manual for additional information. A cracked blade must be referred to an appropriately licensed propeller repair station. INSPECTION AND CHECK Page 5-7 Rev. 17 Jul/12

194 CAUTION: Propeller Owner s Manual DO NOT ATTEMPT TO REPAIR A CRACKED HUB. (3) Visually inspect the hub parts for cracks, or wear. Refer to Grease and Oil Leaks in the Inspection Procedures section of this chapter for procedure. A cracked hub must be referred to an appropriately licensed propeller repair facility. (4) Inspect all visible propeller parts for cracks, wear or unsafe conditions. (5) Check for oil and grease leaks. Refer to Grease or Oil Leakage in the Inspection Procedures section of this chapter for procedure. (6) If a blade track problem is suspected, check the blade track. Refer to Blade Track in the Inspection Procedures section of this chapter. (7) For (-2 and -5) feathering propellers which incorporate an air charge in the cylinder, check pressure every 100 hours or once a month, whichever comes first. Refer to Maintenance Practices chapter of this manual for procedures. (a) If the propeller air pressure is routinely low, or there is engine oil leaking from the air valve, a faulty seal in the propeller should be considered. An inspection to verify the condition should be performed by qualified personnel at an appropriately licensed propeller repair facility. (8) For an unfeathering accumulator, check the air pressure. (a) For a Hartzell Propeller Inc. unfeathering accumulator, check the air pressure every 100 hours or once a month, whichever comes first. 1 For the correct air pressure, refer to Table For procedures to recharge the unfeathering accumulator, refer to the section "Unfeathering Accumulator Air Charge" in the Maintenance Practices chapter of this manual. INSPECTION AND CHECK Page 5-8 Rev. 17 Jul/12

195 Propeller Owner s Manual 3 If the accumulator air pressure is routinely low, or there is engine oil leaking from the air valve, a faulty seal in the accumulator should be considered. An inspection to verify the condition should be performed by qualified personnel at an appropriately licensed propeller repair facility. (b) For a non-hartzell Propeller Inc. unfeathering accumulator, refer to the manufacturer's published data for inspection and check requirements. (9) Check the accuracy of the tachometer. Refer to Tachometer Inspection in the Inspection Procedures section of this chapter. (10) Clean or replace the anti-ice system filter (if an anti-ice system is installed). (11) Make an entry in the propeller logbook about completion of these inspections. B. Blade Inspection for an HC-C2YR-2CLUF/FLC7666A-4 Propeller Installed on OMA SUD Skycar Aircraft CAUTION: ESTABLISH MORE FREQUENT INTERVALS FOR INSPECTION IF SERVICE EXPERIENCE INDICATES THAT SEVERE CORROSION IS FOUND DURING INSPECTIONS. (1) Visually examine each blade for paint erosion and corrosion at intervals not exceeding 200 hours of operation or every 12 calendar months, whichever occurs first. WARNING: CLEANING AGENTS (ACETONE, #700 LACQUER THINNER, AND MEK), ARE FLAMMABLE AND TOXIC TO THE SKIN, EYES, AND RESPIRATORY TRACT. SKIN AND EYE PROTECTION ARE REQUIRED. AVOID PROLONGED CONTACT. USE IN WELL VENTILATED AREA. (a) Using a cloth dampened with actetone, MEK, or MPK, thoroughly clean each blade shank where exposed to engine exhaust and remove all foreign matter/exhaust residue. INSPECTION AND CHECK Page 5-9 Rev. 17 Jul/12

196 Propeller Owner s Manual (b) Paint must be in good condition in the area exposed to exhaust gasses. Repair and repainting is required if: 1 Any of the underlying aluminum blade is exposed. 2 There are any indications of corrosion, such as pitting or any other unusual conditions. (c) All corrosion indications require repair and subsequent repainting by an appropriately licensed propeller repair facility. 1 Refer to FAA Advisory Circular AC 43.4A (or subsequent revision) for additional information about corrosion. This circular provides definitions, repair procedures, safety precautions, etc. (2) If repair and repainting are required, refer to the Blade Repairs section in the Maintenance Practices chapter of this manual for additional information. 1 Qualified personnel must make the determination if repairs can be made locally or must be sent to an appropriately licensed propeller repair facility. Hartzell Propeller Inc. recommends that in borderline or questionable situations it is preferable to send the propeller to an appropriately licensed propeller repair facility. C. Spinner Bulkhead Inspection for an HC-E3YR-1RF Propeller Installed on S.N.A. Inc. Seawind Aircraft. (1) Inspect the spinner bulkhead (P/N D-4877-[ ]) for cracks every 50 flight hours. (2) Visually inspect the spinner bulkhead for cracks around the bulkhead attachment bolts. (3) If a crack is found, the spinner bulkhead must be removed and replaced or referred to an appropriately licensed repair facility for repair. INSPECTION AND CHECK Page 5-10 Rev. 17 Jul/12

197 Propeller Owner s Manual D. Low Pitch Stop Hardware Inspection for a PHC-C3YF-2UF/FC7693DFB Propeller (1) Propellers installed on the following aircraft in accordance with Ram Aircraft STC SA09971SC and with a one piece spinner dome assembly are affected: (a) Cessna T310 (P,Q,R) (b) Cessna 320 (D,E,F) (c) Cessna 340 (A) (d) Cessna 402C (e) Cessna 414 (A) (2) Examine the logbook or visually examine the low pitch stop hardware configuration. (a) If there is an entry that indicates compliance with Hartzell Propeller Inc. Service Bulletin HC-SB or compliance with the low pitch stop hardware modification in this manual, or if a visual examination shows that the hardware configuration is one hex nut safety wired to a set screw, no further action is required. (b) If there is not an entry that indicates compliance with Hartzell Propeller Inc. Service Bulletin HC-SB or compliance with the low pitch stop hardware modification in this manual, or if visual examination shows that the hardware configuration is not one hex nut safety wired to a set screw, modify the propeller assembly to the hardware configuration of one hex nut safety wired to a set screw in accordance with the section "Modification of the Low Pitch Stop Hardware" in the Maintenance Practices chapter of this manual. INSPECTION AND CHECK Page Rev. 21 Mar/15

198 Propeller Owner s Manual (This page is intentionally blank.) INSPECTION AND CHECK Page Rev. 21 Mar/15

199 E. Periodic Maintenance Propeller Owner s Manual (1) Lubricate the propeller assembly. Refer to Lubrication in the Maintenance Practices chapter of this manual for intervals and procedures. F. Airworthiness Limitations (1) Certain components, as well as the entire propeller may have specific life limits established as part of the certification by the FAA. Such limits require mandatory replacement of specified parts after a defined number of hours and/or cycles of use. (2) Life limited component times may exist for the propeller models included in this manual. Refer to the Airworthiness Limitations chapter of this manual. (3) Operators are urged to keep informed of airworthiness information via Hartzell Propeller Inc. Service Bulletins and Service Letters, which are available from Hartzell distributors or from the Hartzell Propeller Inc. factory by subscription. Selected information is also available on Hartzell Propeller s website at G. Overhaul Periods In flight, the propeller is constantly subjected to vibration from the engine and the airstream, as well as high centrifugal forces. The propeller is also subject to corrosion, wear, and general deterioration due to aging. Under these conditions, metal fatigue or mechanical failures can occur. In order to protect your safety, your investment, and to maximize the safe operating lifetime of your propeller, it is essential that a propeller be properly maintained and overhauled according to the recommended service procedures. CAUTION 1: OVERHAUL PERIODS LISTED BELOW, ALTHOUGH CURRENT AT THE TIME OF PUBLICATION, ARE FOR REFERENCE PURPOSES ONLY. OVERHAUL PERIODS MAY BE INCREASED OR DECREASED AS A RESULT OF EVALUATION. INSPECTION AND CHECK Page 5-11 Rev. 21 Mar/15

200 Propeller Owner s Manual CAUTION 2: CHECK THE LATEST REVISION OF HARTZELL PROPELLER INC. SERVICE LETTER HC-SL-61-61Y FOR THE MOST CURRENT INFORMATION. THE SERVICE LETTER IS AVAILABLE ON THE HARTZELL PROPELLER INC. WEBSITE AT (1) Reciprocating Engine Installations (a) Propellers installed on piston engine aerobatic aircraft (certificated as aerobatic or other aircraft routinely exposed to aerobatic use) are to be overhauled at 1000 hours. See paragraph 4.F.(1)(i) for calendar limits. (b) Propellers installed on agricultural aircraft are to be overhauled at 2000 hours. Calendar time is limited to 36 months. These limits apply even if the propeller is later installed on a non-agricultural category aircraft. (c) Propellers installed on Franklin engines are to be overhauled at 1500 hours. See paragraph 4.F.(1)(i) for calendar limits. (d) Two blade propellers manufactured before April 1997 are to be overhauled at 2000 hours. See paragraph 4.F.(1)(i) for calendar limits. (e) Two blade propellers manufactured after April 1997 (identified by a "B" suffix in the propeller serial number) are to be overhauled at 2400 hours. Calendar time is limited to 72 months. (f) Three blade propellers manufactured before 1983 are to be overhauled at 2000 hours. See paragraph 4.F.(1)(i) for calendar limits. (g) Three blade propellers manufactured after 1983 are to be overhauled at 2400 hours. See paragraph 4.F.(1)(i) for calendar limits. (h) Four blade propellers are to be overhauled at 2400 hours. See paragraph 4.F.(1)(i) for calendar limits. INSPECTION AND CHECK Page 5-12 Rev. 17 Jul/12

201 Propeller Owner s Manual (i) Propellers manufactured or overhauled since October 1991 are required to have the internal hub surface painted for additional corrosion protection. Hubs with painted internal surface have a 72 month overhaul calendar limit. Hubs which have not had the internal surface painted have a 60 month overhaul calendar limit until the hub internal surface is painted for corrosion protection. After painting, calendar limit increases to 72 months. (2) Turbine Engine Installations (-5 propellers only) (a) Hartzell Propeller Inc. compact propellers installed on turbine engine aircraft (except for agricultural aircraft) must be overhauled at 3000 hours of operation or 60 calendar months, whichever occurs first. See paragraphs 4.F.(2)(c) for calendar limits. (b) Propellers installed on agricultural aircraft must be overhauled at 3000 hours. Calander time is limited to 36 months. These limits apply even if the propeller is later installed on a non-agricultural category aircraft. (c) Hartzell Propeller Inc. compact propellers installed on turbine engine non-agricultural aircraft have a overhaul calendar limit of 60 calendar months. Propellers manufactured or overhauled since October 1991 are required to have the internal hub surface painted for additional corrosion protection. Hubs with painted internal surface have a 72 month overhaul calendar limit. Hubs which have not had the internal surface painted have a 60 month overhaul calendar limit until the hub internal surface is painted for corrosion protection. After painting, calendar limit increases to 72 months. INSPECTION AND CHECK Page 5-13 Rev. 17 Jul/12

202 Propeller Owner s Manual 5. Inspection Procedures CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS SECTION MAY INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS. REFER TO THE ILLUSTRATED PARTS LIST CHAPTER OF THE APPLICABLE OVERHAUL MANUAL(S) FOR THE IDENTIFICATION OF SPECIFIC PROPELLER CRITICAL PARTS. The following inspections must be made on a regular basis, either before flight, during required periodic inspection, as described in this chapter, or if a problem is noted. Possible corrections to problems discovered during inspections, additional inspections, and limits are detailed in the following inspection procedures. A. Blade Damage Refer to Blade Repairs section in the Maintenance Practices chapter of this manual for information regarding blade damage. B. Grease or Oil Leakage WARNING: UNUSUAL OR ABNORMAL GREASE LEAKAGE OR VIBRATION, WHERE THE CONDITION STARTED SUDDENLY, CAN BE AN INDICATION OF A FAILING PROPELLER BLADE OR BLADE RETENTION COMPONENT. AN INFLIGHT BLADE SEPARATION CAN RESULT IN DEATH, SERIOUS BODILY INJURY, AND/ OR SUBSTANTIAL PROPERTY DAMAGE. UNUSUAL OR ABNORMAL GREASE LEAKAGE OR VIBRATION DEMANDS IMMEDIATE INSPECTION FOR A POSSIBLE CRACKED HUB. INSPECTION AND CHECK Page 5-14 Rev. 17 Jul/12

203 Propeller Owner s Manual NOTE: A new or newly overhauled propeller may leak slightly during the first several hours of operation. This leakage may be caused by the seating of seals and O-rings, and the slinging of lubricants used for seal lubrication during assembly. Such leakage should cease within the first ten hours of operation. Leakage that persists beyond the first ten hours of operation on a new or newly overhauled propeller, or occurs on a propeller that has been in service for some time will require repair. A determination should be made as to the source of the leak. The only leakage that is field repairable is the removal and replacement of the O-ring seal between the engine and propeller flange. All other leakage repairs should be referred to an appropriately licensed propeller repair facility. An instance of abnormal grease leakage should be inspected using the following the procedure: (1) Remove the spinner dome. CAUTION: PERFORM A VISUAL INSPECTION WITHOUT CLEANING THE PARTS. A TIGHT CRACK IS OFTEN EVIDENT DUE TO TRACES OF GREASE EMANATING FROM THE CRACK. CLEANING CAN REMOVE SUCH EVIDENCE AND MAKE A CRACK VIRTUALLY IMPOSSIBLE TO SEE. (2) Perform a visual inspection for cracks in the hub. A crack may be readily visible, or may be indicated by grease leaking from a seemingly solid surface. Extra attention should be given to the blade retention area of the hub. (3) Perform a visual inspection of the hub and blade retention areas to locate the origin of leakage. If the origin of grease leakage is determined to be a noncritical part such as an O-ring or sealant, repairs can be accomplished during scheduled maintenance, as long as flight safety is not compromised. INSPECTION AND CHECK Page 5-15 Rev. 17 Jul/12

204 Propeller Owner s Manual (4) If cracks are suspected, additional inspections must be performed before further flight. These inspections must be performed by qualified personnel at an appropriately licensed propeller repair facility to verify the condition. Such inspections typically include disassembly of the propeller followed by inspection of parts, using nondestructive methods in accordance with published procedures. (5) If cracks or failing components are found, parts must be replaced before further flight. Report such incidents to the appropriate airworthiness authorities and Hartzell Propeller Inc. Product Support. C. Vibration Instances of abnormal vibration should be investigated immediately. If the cause of the vibration is not readily apparent, the propeller may be inspected following the procedure below: NOTE: It may be difficult to readily identify the cause of abnormal vibration. It may originate in the engine, propeller, or airframe. Troubleshooting procedures typically initiate with investigation of the engine. Airframe components (such as engine mounts or loose landing gear doors) can also be the source of vibration. When investigating an abnormal vibration, the possibility of a failing blade or blade retention component should be considered as a potential source of the problem. (1) Perform troubleshooting and evaluation of possible sources of vibration in accordance with engine or airframe manufacturer's instructions. (2) Refer to the Vibration section in the Testing and Troubleshooting chapter of this manual. Perform the checks to determine possible cause of the vibration. If no cause is found, then consider that the origin of the problem could be the propeller and proceed with steps 4.C.(3) through 4.C.(8) in this chapter. (3) Remove the spinner dome. INSPECTION AND CHECK Page 5-16 Rev. 17 Jul/12

205 Propeller Owner s Manual (4) Perform a visual inspection for cracks in the hub. (a) Pay particular attention to the blade retention areas of the hub. (b) A crack may be readily visible or may be indicated by grease leaking from a seemingly solid surface. (5) If cracks are suspected, additional inspections must be performed before further flight. These inspections must be performed by qualified personnel at an appropriately licensed propeller repair facility to verify the condition. Such inspections typically include disassembly of the propeller, followed by inspection of parts, using nondestructive methods in accordance with published procedures. (6) Check the blades and compare blade-to-blade differences: (a) Inspect the propeller blades for unusual looseness or movement. Refer to the Loose Blades section of this chapter. (b) Check blade track. Refer to the Blade Track section of this chapter. CAUTION: DO NOT USE BLADE PADDLES TO TURN THE BLADES. (c) Manually (by hand) attempt to turn the blades (change pitch). (d) Visually check for damaged blades. (7) If abnormal blade conditions or damage are found, perform additional inspections by qualified personnel at an appropriately licensed propeller repair facility to evaluate the condition. Refer to the Blade Repairs section in the Maintenance Practices chapter of this manual. (8) If cracks or failing components are found, these parts must be replaced before further flight. Report such incidents to airworthiness authorities and Hartzell Propeller Inc. Product Support. INSPECTION AND CHECK Page 5-17 Rev. 17 Jul/12

206 D. Tachometer Inspection NOTE: Propeller Owner s Manual An appropriately licensed propeller repair facility may also be able to perform a mechanical tachometer inspection. WARNING: OPERATION WITH AN INACCURATE TACHOMETER MAY RESULT IN RESTRICTED RPM OPERATION AND DAMAGING HIGH STRESSES. BLADE LIFE WILL BE SHORTENED AND COULD RESULT IN CATASTROPHIC FAILURE. (1) Using a calibrated external device capable of displaying propeller RPM, verify the accuracy of a mechanical engine tachometer at 100 hour intervals or at annual inspection, whichever occurs first. (2) Hartzell Propeller Inc. recommends calibrating the aircraft using a tachometer that is accurate within +/- 10 RPM, has NIST calibration (traceable), and has an appropriate calibration schedule. APS6155 Checking Blade Track Figure 5-1 INSPECTION AND CHECK Page 5-18 Rev. 22 Jul/16

207 E. Blade Track (1) Check blade track as follows: Propeller Owner s Manual (a) Chock the aircraft wheels securely. (b) Refer to Figure 5-1. Place a fixed reference point beneath the propeller, within 0.25 inch (6.0 mm) of the lowest point of the propeller arc. NOTE: This reference point may be a flat board with a sheet of paper attached to it. The board may then be blocked up to within 0.25 inch (6.0 mm) of the propeller arc. WARNING: MAKE SURE THE ENGINE MAGNETO IS GROUNDED (OFF) BEFORE ROTATING THE PROPELLER. (c) Rotate the propeller by hand (opposite the direction of normal rotation) until a blade points directly at the reference surface (paper). 1 If the propeller does not have a start lock and blade track must be checked when the propeller is in feather position: a Put a spirit level or blade protractor against the flat side of the blade counterweight. b Slightly rotate the propeller blade until the level or protractor indicates the blade counterweight is perpendicular with the reference surface (paper). (d) Mark the position of the blade tip in relation to the reference surface (paper). (e) Repeat this procedure with the remaining blades. (f) Tracking tolerance is ± inch (1.57 mm) or inch (3.17 mm) total. (2) Possible Correction (a) Remove foreign matter from the propeller mounting flange. (b) If no foreign matter is present, refer to an appropriately licensed propeller repair facility. INSPECTION AND CHECK Page 5-19 Rev. 17 Jul/12

208 F. Loose Blades Propeller Owner s Manual Refer to Figure 5-2. Limits for blade looseness are as follows: End Play (leading edge to trailing edge) See Note below Fore & Aft Movement (Face to camber See Note below In & Out None Radial Play (pitch change) ± 0.5 degree (1 degree total) measured at reference station NOTE: Blades are intended to be tight in the propeller, however slight movement is acceptable if the blade returns to its original position when released. Blades with excessive movement, or that do not return to their original position when released may indicate internal wear or damage which should be referred to an appropriately licensed propeller repair facility. IN AND OUT PLAY FORE AND AFT PLAY BLADE END PLAY RADIAL PLAY APS6163 Blade Play Figure 5-2 INSPECTION AND CHECK Page 5-20 Rev. 22 Jul/16

209 Propeller Owner s Manual G. Corrosion WARNING: REWORK THAT INVOLVES COLD WORKING THE METAL, RESULTING IN CONCEALMENT OF A DAMAGED AREA IS NOT PERMITTED. (1) Light corrosion on the blades or counterweights may be removed by qualified personnel in accordance with the Blade Repairs section in the Maintenance Practices chapter of this manual. (2) Heavy corrosion that results in severe pitting must be referred to an appropriately licensed propeller repair facility. H. Spinner Damage (1) Inspect the spinner for cracks, missing hardware, or other damage. (a) For metal spinners, refer to Hartzell Propeller Inc. Manual 127 ( ) or an appropriately licensed propeller repair facility for spinner damage acceptance and repair information. Contact the local airworthiness authority for repair approval. (b) For composite spinners, refer to Hartzell Propeller Inc. Manual 148 ( ) or an appropriately licensed propeller repair facility for spinner damage acceptance and repair information. Contact the local airworthiness authority for repair approval. I. Electric De-ice System (1) Refer to the Anti-ice and De-ice Systems chapter of this manual for inspection procedures. J. Anti-ice System (1) Refer to the Anti-ice and De-ice Systems chapter of this manual for inspection procedures. INSPECTION AND CHECK Page 5-21 Rev. 22 Jul/16

210 Propeller Owner s Manual Requires Evaluation by an Appropriately Licensed Propeller Repair Facility No Action Required 20 Sec 1 min 3 min 5 min Duration of Overspeed Reciprocating Engine Overspeed Limits Figure % 105% 103% Percent Overspeed -- Reciprocating Engines Only INSPECTION AND CHECK Page 5-22 Rev. 17 Jul/12

211 Propeller Owner s Manual 125% 120% 115% 110% 106% 20 Requires Evaluation by an Appropriately Licensed Propeller Repair Facility No Action Required Duration of Overspeed (in seconds) Duration of Overspeed in Seconds Turbine Engine Overspeed Limits Figure 5-4 Percent Overspeed -- Turbine Engines Only INSPECTION AND CHECK Page 5-23 Rev. 17 Jul/12

212 Propeller Owner s Manual 120% 115% 110% 102% 20 Requires Evaluation by an Appropriately Licensed Propeller Repair Facility No Action Required Duration of Overtorque in Seconds Turbine Engine Overtorque Limits Figure Percent Overtorque -- Turbine Engines Only INSPECTION AND CHECK Page 5-24 Rev. 17 Jul/12

213 Propeller Owner s Manual 6. Special Inspections CAUTION: INSTRUCTIONS AND PROCEDURES IN THIS SECTION MAY INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS. REFER TO THE ILLUSTRATED PARTS LIST CHAPTER OF THE APPLICABLE OVERHAUL MANUAL(S) FOR THE IDENTIFICATION OF SPECIFIC PROPELLER CRITICAL PARTS. A. Overspeed/Overtorque An overspeed occurrs when the propeller RPM exceeds the maximum RPM stated in the applicable Aircraft Type Certificate Data Sheet. An overtorque condition occurs when the engine load exceeds the limits established by the engine, propeller, or airframe manufacturer. The duration of time at overspeed/overtorque for a single event determines the corrective action that must be taken to make sure no damage to the propeller has occurred. The criteria for determining the required action after an overspeed are based on many factors. The additional centrifugal forces that occur during overspeed are not the only concern. Some applications have sharp increases in vibratory stresses at RPMs above the maximum rated for the airframe/engine/propeller combination. (1) When a propeller installed on a reciprocating engine has an overspeed event, refer to the Reciprocating Engine Overspeed Limits (Figure 5-3) to determine the corrective action to be taken. (2) When a propeller installed on a turbine engine has an overspeed event, refer to the Turbine Engine Overspeed Limits (Figure 5-4) to determine the corrective action to be taken. (3) When a propeller installed on a turbine engine has an overtorque event, refer to the Turbine Engine Overtorque Limits (Figure 5-5) to determine the corrective action to be taken. (4) Make an entry in the propeller logbook about the overspeed/overtorque event. INSPECTION AND CHECK Page 5-25 Rev. 17 Jul/12

214 Propeller Owner s Manual B. Lightning Strike CAUTION: ALSO CONSULT ENGINE AND AIRFRAME MANUFACTURER'S MANUALS. THERE MAY BE ADDITIONAL REQUIREMENTS SUCH AS DE-ICE AND ENGINE SYSTEM CHECKS TO PERFORM AFTER A PROPELLER LIGHTNING STRIKE. (1) General (a) In the event of a propeller lightning strike, an inspection is required before further flight. It may be permissible for a propeller to be operated for an additional ten (10) hours if the propeller is not severely damaged and meets the requirements in paragraph 5.B.(2). (b) Regardless of the outcome of the initial inspection, the propeller must be removed from the aircraft, disassembled, evaluated, and/or repaired by an appropriately licensed propeller repair facility. (2) Procedure for Temporary Operation If temporary additional operation is desired before propeller removal and disassembly: (a) Remove spinner dome and perform visual inspection of propeller, spinner, and de-ice system for evidence of significant damage that would require repair before flight (such as broken de-ice wires or arcing damage to propeller hub). CAUTION: IF THE PROPELLER EXPERIENCES A LIGHTNING STRIKE,THE ALUMINUM BLADES MUST BE WITHIN AIRWORTHY LIMITS FOR ANY ADDITIONAL FLIGHT. (b) If the only evident damage is slight arcing burns to the blades, then operation for ten (10) hours is acceptable before disassembly and inspection. (c) Perform a functional check of the propeller deice system (if installed) in accordance with aircraft maintenance manual procedures. INSPECTION AND CHECK Page 5-26 Rev. 17 Jul/12

215 Propeller Owner s Manual (d) Regardless of the degree of damage, make an entry in the propeller logbook about the lightning strike. (e) The propeller must be removed from the aircraft, disassembled, evaluated, and/or repaired by an appropriately licensed propeller repair facility for flight beyond the temporary operation limits granted above. C. Foreign Object Strike (1) General (a) A foreign object strike can include a broad spectrum of damage, from a minor stone nick to severe ground impact damage. A conservative approach in evaluating the damage is required because there may be hidden damage that is not readily apparent during an on-wing, visual inspection. (b) A foreign object strike is defined as: 1 Any incident, whether or not the engine is operating, that requires repair to the propeller other than minor dressing of the blades. Examples of foreign object strike include situations where an aircraft is stationary and the landing gear collapses causing one or more blades to be significantly damaged, or where a hangar door (or other object) strikes the propeller blade. These cases should be handled as foreign object strikes because of potentially severe side loading on the propeller hub, blades and retention bearings. 2 Any incident during engine operation in which the propeller impacts a solid object that causes a drop in revolutions per minute (RPM) and also requires structural repair of the propeller (incidents requiring only paint touch-up are not included). This is not restricted to propeller strikes against the ground. 3 A sudden RPM drop while impacting water, tall grass, or similar yielding medium, where propeller blade damage is not normally incurred. INSPECTION AND CHECK Page 5-27 Rev. 17 Jul/12

216 (2) Procedure Propeller Owner s Manual (a) In the event of a foreign object strike, an inspection is required before further flight. If the inspection reveals one or more of the following indications, the propeller must be removed from the aircraft, disassembled and overhauled in accordance with the applicable propeller and blade maintenance manuals. 1 A loose blade in the hub. 2 Any noticeable or suspected damage to the pitch change mechanism. 3 A bent blade (out of track or angle). 4 Any blade diameter reduction. 5 A bent, cracked, or failed engine shaft. 6 Vibration during operation that was not present before the event. (b) Nicks, gouges, and scratches on blade surfaces or the leading and trailing edges must be removed before flight. Refer to the Blade Repairs section in the Maintenance Practices chapter of this manual. (c) For engine mounted accessories - for example, governors, pumps, and propeller control units manufactured by Hartzell Propeller Inc. - if the foreign object strike resulted in a sudden stop of the engine, the unit must be disassembled and inspected in accordance with the applicable maintenance manual. (d) Regardless of the degree of damage, make a log book entry to document the foreign object strike incident and any corrective action(s) taken. INSPECTION AND CHECK Page 5-28 Rev. 17 Jul/12

217 D. Fire Damage or Heat Damage Propeller Owner s Manual WARNING: HUBS ARE MANUFACTURED FROM HEAT TREATED FORGINGS AND ARE SHOT PEENED. BLADES ARE MANUFACTURED FROM HEAT TREATED FORGINGS AND ARE COMPRESSIVELY ROLLED AND SOMETIMES SHOT PEENED. EXPOSURE TO HIGH TEMPERATURES CAN DESTROY THE FATIGUE BENEFITS OBTAINED FROM THESE PROCESSES. (1) On rare occasions propellers may be exposed to fire or heat damage such as an engine or hangar fire. In the event of such an incident, an inspection by an appropriately licensed propeller repair facility is required before further flight. 7. Long Term Storage A. Parts shipped from the Hartzell Propeller Inc. factory are not shipped or packaged in a container that is designed for long term storage. B. Long term storage procedures may be obtained by contacting a Hartzell Propeller Inc. distributor, or the Hartzell Propeller Inc. factory via the Product Support number listed in the Introduction chapter of this manual. Storage information is also detailed in Hartzell Propeller Inc. Standard Practices Manual 202A ( ). C. Information regarding the return of a propeller assembly to service after long term storage may be obtained by contacting a Hartzell Propeller Inc. distributor, or the Hartzell Propeller Inc. factory via the Product Support number listed in the Introduction chapter of this manual. This information is also detailed in Hartzell Propeller Inc. Standard Practices Manual 202A ( ). INSPECTION AND CHECK Page 5-29 Rev. 17 Jul/12

218 Propeller Owner s Manual (This page is intentionally blank.) INSPECTION AND CHECK Page 5-30 Rev. 17 Jul/12

219 MAINTENANCE PRACTICES - CONTENTS 1. Cleaning A. General Cleaning B. Spinner Cleaning and Polishing Lubrication A. Lubrication Intervals B. Lubrication Procedure C. Approved Lubricants Air Charge (-2 and -5 Propellers) A. Charging the Propeller B. Basic pressures Unfeathering Accumulator Air Charge A. Charging a Hartzell Propeller Inc. Accumulator Blade Repairs A. Repair of Nicks or Gouges B. Repair of Bent Blades Painting After Repair A. General B. Painting of Aluminum Blades Dynamic Balance A. Overview B. Inspection Procedures Before Balancing C. Modifying Spinner Bulkhead to Accommodate Dynamic Balance Weights D. Placement of Balance Weights for Dynamic Balance Propeller Low Pitch Setting A. Low Pitch Stop - All Propeller Models B. Max. RPM (Static) Low Pitch Stop Adjustment C. Modification of the Low Pitch Stop Hardware Propeller High Pitch Settings A. High Pitch (Min. RPM) Stop or Feathering Pitch Stop Start Lock Settings A. Start Lock Pitch Stop Propeller Ice Protection Systems A. Electric De-ice System B. Anti-ice System MAINTENANCE PRACTICES Page 6-1 Rev. 22 Jul/16

220 LIST OF FIGURES Lubrication Fitting and Air Charge Valve Location... Figure Lubrication Fitting... Figure Lubrication Label... Figure Counterweighted vs Non-Counterweighted Blades... Figure Unfeathering Accumulator... Figure Repair Limitations... Figure Low Pitch Stop Adjustment (-1, -4)... Figure Low Pitch Stop Adjustment (-2, -5) For Propellers That Use a Two-piece Spinner Dome... Figure Low Pitch Stop Adjustment (-2, -5) For Propellers That Use a One-piece Spinner Dome... Figure Hex Nut Configuration... Figure LIST OF TABLES Air Charge Pressure... Table Air Charge Pressure... Table Air Charge Pressure... Table Air Charge Pressure... Table Air Charge Pressure... Table Air Charge Pressure... Table Air Charge Pressure... Table Air Charge Pressure... Table Air Charge Pressure... Table Air Charge Pressure... Table Accumulator Air Charge Pressure... Table Approved Touch-up Paints... Table MAINTENANCE PRACTICES Page 6-2 Rev. 22 Jul/16

221 1. Cleaning CAUTION 1: INSTRUCTIONS AND PROCEDURES IN THIS SECTION MAY INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS. REFER TO THE ILLUSTRATED PARTS LIST CHAPTER OF THE APPLICABLE OVERHAUL MANUAL(S) FOR THE IDENTIFICATION OF SPECIFIC PROPELLER CRITICAL PARTS. CAUTION 2: A. General Cleaning DO NOT USE PRESSURE WASHING EQUIPMENT TO CLEAN THE PROPELLER OR CONTROL COMPONENTS. PRESSURE WASHING CAN FORCE WATER AND/OR CLEANING FLUIDS PAST SEALS AND LEAD TO INTERNAL CORROSION OF PROPELLER COMPONENTS. CAUTION 1: CAUTION 2: WHEN CLEANING THE PROPELLER, DO NOT PERMIT SOAP OR SOLVENT SOLUTIONS TO RUN OR SPLASH INTO THE HUB AREA. DO NOT CLEAN PROPELLER WITH CAUSTIC OR ACIDIC SOAP SOLUTIONS. IRREPARABLE CORROSION OF PROPELLER COMPONENTS MAY OCCUR. CAUTION 3: DO NOT USE ANY SOLVENT DURING CLEANING THAT COULD SOFTEN OR DESTROY THE BOND BETWEEN CHEMICALLY ATTACHED PARTS. (1) To remove grease or oil from propeller surfaces, apply Stoddard Solvent or equivalent to a clean cloth and wipe the part clean. (2) Using a noncorrosive soap solution, wash the propeller. (3) Thoroughly rinse with water. (4) Permit to dry. MAINTENANCE PRACTICES Page 6-3 Rev. 17 Jul/12

222 LUBRICATION FITTING (ENGINE SIDE HUB HALF) LUBRICATION FITTING (CYLINDER SIDE HUB HALF) Lubrication Fitting and Air Charge Valve Location Figure 6-1 APS6156 AIR CHARGE VALVE (-2 AND -5 PROPELLERS ONLY) MAINTENANCE PRACTICES Page 6-4 Rev. 14 Jan/09

223 B. Spinner Cleaning and Polishing 2. Lubrication CAUTION: Propeller Owner's Manual (1) Clean spinner using the General Cleaning procedures above. (2) Polish the dome, if necessary, with an automotive-type aluminum polish. INSTRUCTIONS AND PROCEDURES IN THIS SECTION MAY INVOLVE PROPELLER CRITICAL PARTS. REFER TO THE INTRODUCTION CHAPTER OF THIS MANUAL FOR INFORMATION ABOUT PROPELLER CRITICAL PARTS. REFER TO THE ILLUSTRATED PARTS LIST CHAPTER OF THE APPLICABLE OVERHAUL MANUAL(S) FOR THE IDENTIFICATION OF SPECIFIC PROPELLER CRITICAL PARTS. A. Lubrication Intervals (1) The propeller must be lubricated at intervals not to exceed 100 hours or at 12 calendar months, whichever occurs first. (a) If annual operation is significantly less than 100 hours, calendar lubrication intervals should be reduced to six months. (b) If the aircraft is operated or stored under adverse atmospheric conditions, e.g., high humidity, salt air, calendar lubrication intervals should be reduced to six months. (2) Owners of high use aircraft may wish to extend their lubrication interval. Lubrication interval may be gradually extended after evaluation of previous propeller overhauls with regard to bearing wear and internal corrosion. MAINTENANCE PRACTICES Page 6-5 Rev. 21 Mar/15

224 Cylinder Lubrication Fitting or Lubrication Hole Plug Removed From the Cylinder-side Hub Half Lubrication Fitting Installed in the Engine-side Hub Half Inspection Mirror NOTE: A 2-blade propeller is shown for illustration purposes only. TI Lubrication Fitting Figure 6-2 MAINTENANCE PRACTICES Page 6-6 Rev. 22 Jul/16